T-6 Systems 1 Review 1

Front 1

Which control surface controls the aircraft movement around the pitch axis?

Back 1

Elevator

Front 2

The Trim Aid Device (TAD) assists trimming for which control surface during airspeed and power changes?

Back 2

The TAD senses torque, altitude, airspeed, and pitch rate and computes a desired rudder trim tab position

Front 3

True or False? Engine exhaust augments the thrust of the propeller.

Back 3

True. Exhaust gases are ejected rearward providing thrust which augments that produced by the propeller.

Front 4

Primary aircraft electrical power is provided by which component of the electrical system?

Back 4

The generator function of the starter/generator

Front 5

Tuning for each of the communications and navigation radios and the transponder is provided by which component?

Back 5

RMU

Front 6

True or False? The VHF navigation system provides VOR, ILS, Localizer and GPS capability.

Back 6

False. The VHF system provides VOR, ILS, localizer, and glideslope capability

Front 7

Primary navigation display is provided by which component of the Electronic Flight Instrument System (EFIS)

Back 7

Electronic Horizontal Situation Indicator (EHSI)

Front 8

Which Standby flight instruments will operate without electrical power?

Back 8

The standby altimeter, airspeed indicator, the ball in the turn and bank indicator, and the magnetic compass.

Front 9

True or False? The entire canapy structure is engineered to be protected from birdstrikes?

Back 9

False. Only the windscreen and front canopy transparency are protected.

Front 10

Landing gear extension and retraction is operated by which aircraft system?

Back 10

Hydraulic

Front 11

Movement around the roll axis is controlled by which primary control surface?

Back 11

Ailerons

Front 12

What coponent of the ejection seat provides sufficient altitude for parachute deployment?

Back 12

Rocket Motor

Front 13

True or False? The magnetic compass is one of the primary flight instruments.

Back 13

False. The magnetic compass is a standby instrument.

Front 14

Secondary aircraft electrical power is provided by what component?

Back 14

24 volt battery

Front 15

Which aircraft system provides automatic temperature and pressure control?

Back 15

Environmental Control System

Front 16

Control of the transponder is provided by which component?

Back 16

Radio Management Unit (RMU)

Front 17

True or False? The canopy is hinged at the rear and opens up.

Back 17

False. The canopy is hinged along the right side and opens to that side.

Front 18

Which primary instrument provides primary attitude display?

Back 18

Electronic Attitude Director Indicator (EADI)

Front 19

In the event of inadvertent aircraft contact with the ground, which component will be activated and generate a radio signal?

Back 19

The personal locator radio beacon senses impact loads and generates a signal on 121.5 and 243.0 MHz or 121.5 and 406.0 MHz

Front 20

The ailerons control movement of the aircraft in the ____ axis.

Back 20

Longitudinal or roll

Front 21

Which of following is not part of aileron control system. L&R aileron, Bellcranks, TAD, Push-Pull rods, Fr and Rr control sticks

Back 21

TAD

Front 22

True or False? The elevator controls aircraft movement around the lateral or pitch axis.

Back 22

True

Front 23

What is the purpose of the bobweight located on theforward control stick?

Back 23

Enhances control feedback and helps prevent overstressing of the airframe.

Front 24

The rudder controls aircraft movement around the vertical or yaw axis. True or False?

Back 24

True.

Front 25

Rudder pedal position is adjusted with a hand crank located _____.

Back 25

lower portion of the center console

Front 26

Which flight control electromechanical trim system(s) utilize movement of the actual primary control surface?

Back 26

Aileron

Front 27

In the event of conflicting aileron or elevator trim inputs from the front and rear cockpit, the front cockpit input will take priority.

Back 27

False

Front 28

Visual indication of pitch, roll, and yaw trim can be found on the ________.

Back 28

Trim position indicators located on both trim control panels.

Front 29

A primary purpose of the TAD systemis to?

Back 29

Assist the pilot in maintaining directional trim.

Front 30

The TAD computes input to the rudder trim system based on what?

Back 30

engine torque, Airspeed, Altitude, and pitch rate

Front 31

In addition to the TRIM OFF annunciator, actuating the trim interrupt button will also illuminate the _____ annunciator light.

Back 31

TAD OFF

Front 32

What control surfaces are locked when the gust lock is engaged?

Back 32

Elevator, Rudder, Aileron

Front 33

The primary aircraft flight controls consist of what?

Back 33

Ailerons, elevator and rudder

Front 34

Which of the following best describes the function of the aircraft's elevator

Back 34

The elevator system is used to cause movement in the lateral or pitch axis.

Front 35

The aileron ground adjustable trim tabs are for maintenance use only and should not be tampered with by the aircrew. True/False?

Back 35

True

Front 36

Which statement best describes the purpose of the bobweight attached to the forward control stick?

Back 36

Provides higher stick forces as G-loading increases, helps prevent overstressing the airframe

Front 37

Which of the following is NOT included in the rudder control system. Centering Springs, Cables, Bellcrank, Bobweight

Back 37

Bobweight

Front 38

Pilot control of aileron trim is accomplished by movement of an electromechanical trim tab installed on the right aileron. True or False?

Back 38

False

Front 39

The Trim Aid Device (TAD) computer relays trim input to the?

Back 39

rudder trim tab actuator

Front 40

The TAD maintains a takeoff trim setting until ___ KIAS and no weight on the wheels.

Back 40

80

Front 41

A green TAD OFF annunciator will illuminate when ____.

Back 41

The TRIM AID switch is set to off

Front 42

The flight control gust lock is used to _____.

Back 42

lock the primary flight control surfaces when parked.

Front 43

What are the four devices operated by the primary hydraulic system under normal operations?

Back 43

Landing gear/main gear inboard doors, flaps, speed brake and nose wheel steering

Front 44

The hydraulic system and the return side of the power package reservoir are pressurized to which levels respectively?

Back 44

3000 +- 120 and 50 psi

Front 45

When you select a cockpit control to lower flaps, which element of the primary hydraulic system is responsible for activating the corresponding actuator?

Back 45

Electrical selector valve

Front 46

During the loss of engine power, the primary hydraulic system, or the battery bus, the emergency package will allowe a one-time extension of _____.

Back 46

flaps, landing gear and main gear inboard doors

Front 47

The emergency package's manifold contains what?

Back 47

2 emergency extension selector valves

Front 48

What is the purpose of the pressure release valve in the emergency hydraulic system?

Back 48

To automatically release pressure should it reach 3500 psi

Front 49

When the EHYD PX LO annunciator illuminates, it means that emergency accumulator hydraulic pressure is below _____ +- 150 psi

Back 49

2400 psi

Front 50

Which set of landing gear doors are operated hydraulically?

Back 50

The main gear inboard doors

Front 51

A red light illuminated in the landing gear selector handle indicates that the PCL is approaching IDLE, with the gear handle up, or what?

Back 51

The landing gear doors are not closed.

Front 52

What airspeed do you have to be in order to lower the landing gear?

Back 52

Below 150 KIAS

Front 53

What is the function of the emergency landing gear extension handle?

Back 53

It activates the emergency system

Front 54

The engine driven pump pressurizes the hydraulic system to what pressure?

Back 54

3000 +- 120

Front 55

The primary hydraulic system operates what?

Back 55

Landing gear, main gear inboard doors, flaps, nose wheel steering and speed brake

Front 56

What lowers pressure in order to protect the pump?

Back 56

A piston in the power package reservoir

Front 57

The primary hydraulic system's selector manifold contains what?

Back 57

Electrical selector valves

Front 58

Two specific condition in which the emergency hydraulic system is used are?

Back 58

Loss of engine power or the primary hydraulic system fails

Front 59

The emergency hydraulic system specifically operates which of the following?

Back 59

Landing gear, main gear inboard doors, and flaps

Front 60

The emergency package receives its pressure from which of the following?

Back 60

From the emergency accumulator

Front 61

The amber EHYD PX LO annunciator lilght means what?

Back 61

Pressure int eh emergency accumulator is below 2400 +- 150

Front 62

The HYDR FL LO annunciator means?

Back 62

Reservoir fluid level is below 1 Qt

Front 63

When the power package slide valve closes, the hydraulic pump pressure is prevented from energizing any hydraulic components except for the ____.

Back 63

Nose wheel steering actuator

Front 64

What does using flaps in the landing setting allow you to do?

Back 64

Maintain approach glidepath while reducing airspeed

Front 65

What happens if the primary hydraulic system fails?

Back 65

The flaps can be operated using the emergency system package.

Front 66

Before operating the flaps using the emergency system, you must ______.

Back 66

Lower the landing gear using the emergency system

Front 67

Which of the follwoing is a critical limitation of the speed brake?

Back 67

The speed brake does not operate using the emergency hydraulic system

Front 68

Where does the pressure come from that creates the mechanical force to extend the speed brake?

Back 68

From the primary hydraulic system

Front 69

What is an important difference between using the NWS and differential braking.

Back 69

NWS is more sensitive. Differential braking has a tighter turning radius.

Front 70

What happens to NWS if the primary hydraulic system fails?

Back 70

The NWS system will be inoperative and use of rudder and or differential braking on the ground will be necessary

Front 71

True/False? The wheel brake system will continue to operate if the primary hydraulic system fails.

Back 71

True

Front 72

How do you activate the parking brake?

Back 72

Pull and turn the handle 90 degrees clockwise while pushing on the toe brakes

Front 73

Is the NWS part of the selector manifold?

Back 73

No. The NWS is seperate from the selector manifold.

Front 74

Will the NWS operate if primary hydraulic system fails?

Back 74

No.

Front 75

What component specifically ensures the nose wheel is properly aligned before it is retracted or extended?

Back 75

Centering Valve

Front 76

Engaging NWS at high speeds can result in ____

Back 76

Directional control problems due to increased sensitivity

Front 77

What are the functions of the speed brake?

Back 77

Decelerate, and increase descent rate without increasing airspeed.

Front 78

Will the speed brake operate with the emergency system?

Back 78

No

Front 79

What will cause the speed brake to retract?

Back 79

PCL - MAX, Flaps extended, Speed brake switch is moved forward.

Front 80

If the flap indicator fails, how can flap extension be confirmed?

Back 80

Observing a slight nose up tendency

Front 81

Can you operate the emergency flaps running off of auxillary battery as the only source of electrical power?

Back 81

No.

Front 82

Before lowering the flaps, what airspeed do you have to be below?

Back 82

150 KIAS

Front 83

Which component is responsible for sending pressure to the main wheel brakes?

Back 83

Master Cylinder

Front 84

The ____ is interconnected with the elevator trim tab actuator to automatically input pitch trim to compensate for pitch effects as it is operated

Back 84

Speed Brake

Front 85

The ailerons control aircraft movement around which axis?

Back 85

Longitudinal (roll)

Front 86

What are the aileron trailing edge traveling limits

Back 86

20 up 11 down

Front 87

How are the ailerons mass balanced and what function does this perform?

Back 87

Small weights placed on hinge line. Keeps the center of gravity at the pivot point.

Front 88

What is the function of the bobweight?

Back 88

Provides for heavier stick feel when G-load is increasing. Helps prevent overstressing of the aircraft frame

Front 89

What is the purpose of the elevator system?

Back 89

It controls the pitch angle of the aircraft around lateral axis

Front 90

If you move the control stick forward in flight, how will the aircraft react?

Back 90

Elevator trailing edge deflects downward and aircraft nose pitches down

Front 91

What is the purpose of the Rudder system?

Back 91

It controls the aircraft's yaw movement around the vertical (yaw) axis

Front 92

What happens when you step on the right rudder pedal?

Back 92

Moves tail left & Causes aircraft nose to yaw right

Front 93

How does the pilot adjust the rudder pedals to position them at a more convenient setting?

Back 93

By rotating the pedal adjustment hand crank

Front 94

Which primary flight control surface actually moves as part of the trim system?

Back 94

The Ailerons

Front 95

Where are the trim controls for the aileron trim setting, the elevator trim setting and the rudder trim setting?

Back 95

- Elevator/aileron trim switch located at the top of control stick. - Rudder trim switch is located on the PCL in each cockpit

Front 96

What is the function of the trim disconnect switch?

Back 96

It removes power from the trim system and disengages the Trim Aid Device (TAD)

Front 97

What are the indications the trim disconnect switch has been selected?

Back 97

The green TRIM OFF and TAD OFF annunciator lights will be illuminated

Front 98

How is electrical power provided to operate the aileron and elevator trim system?

Back 98

Through a circuit breaker placarded AIL/EL TRIM located on the battery busbreaker panel in front cockpit

Front 99

If gust lock is installed how will the primary flight controls positioned?

Back 99

Ailerons and Rudder in NEUTRAL and Elevator in Nose Down

Front 100

What component is the source of pressure for the primary hydraulic system

Back 100

Engine driven pump

Front 101

What are the normal operating ranges for the hydraulic system pressure and fluid quantity?

Back 101

Pressure at 2880-3120 psi on Engine/Systems/NACWS display. FULL AS or FULL AD displayed on the green indicating rod in reservoir level window

Front 102

What is the maximum speed to operate the landing gear?

Back 102

150 KIAS

Front 103

When is the emergency landing gear extension system used?

Back 103

Loss of primary hydraulic system or batt. bus power or Engine failure

Front 104

What is the sequence for lowering the Emergency landing gear?

Back 104

Lower the landing gear selector handle. Pull the emergency landing gear extension handle.

Front 105

Can flaps be operated in the event of primary hydraulic system failure?

Back 105

Yes, after landing gear has been lowered with emergency system.

Front 106

Where is speed brake Circuit braker located?

Back 106

Front cockpit generator bus

Front 107

What are the indications of abnormal primary flight control operations?

Back 107

Uncommanded pitch, roll or yaw movements, sluggish response to control inputs.

Front 108

What is the corrective action if you have a runaway trim?

Back 108

Perform runaway trim checklist procedures

Front 109

Once takeoff trim is set, the TAD will make no further trim inputs until ___.

Back 109

you reach 80 KIAS and there is no weight on wheels

Front 110

What causes the EHYD PX LO annunciator light to illuminate?

Back 110

Emergency accumulator is less than 2400 psi +- 150

Front 111

Can you operate the wheel brakes if you lose the Primary hydraulic system?

Back 111

Yes the wheel brake system is seperate from the primary and emergency hydraulic system