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T38C Systems > SY1115-6 Flight Contorl and Hyfdraulics > Flashcards

SY1115-6 Flight Contorl and Hyfdraulics Flashcards

1
Q

How many hydraulic systems?

A

2 systems driven by respective engine driven hydraulic pump

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2
Q

Is the reservoirs pressurized?

A

Yes, by 8th stage of compressor to prevent foaming

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3
Q

What powers the hydraulic system pressure

A

airframe mounted gearbos

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4
Q

Which system goes with which engine

A
  • Left Engine Powers the 3,000 PSI Utility System

- Right Engine Powers the 3,000 PSI Flight Control System

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5
Q

Is there any interchange under norm ops

A

No, only if one system fails

-35 Minutes If Either System Reads 0 PSI

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6
Q

Pressure Indicators and Caution Lights are ______to Each System

A

independent

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7
Q

Flight Control Hydraulics power

A

Flight Controls

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8
Q

Utility Hydraulics power

A
  • Flight Controls
  • Augmentation (SAS)
  • Nose Wheel Steering
  • Gear Extension/Retraction
  • Speed Brake
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9
Q

Pressure Indicators powered by

A

AC

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10
Q

Low Pressure or High Temperature cause WCA illumination

A
  • Low Pressure @ 1,500 PSI Illuminates and 1,800 PSI is Needed to Terminate
  • 35 Minutes If Either System Reads 0 PSI
  • High Temperature & Normal Temperature is Needed to Terminate
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11
Q

Shift Mechanism Maintains AC Output Between ______ cycles per sec

A

320 and 480 Cycles Per Second

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12
Q

Gearbox Shift Occurs Between

A

65%-75%

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13
Q

With one system at zero psi

A

Limits Flight Time to 35 Minutes

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14
Q

Conventional Aerodynamic Feel in the Control Stick is Provided Artificially

A

Springs and Bob Weights

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15
Q

Each Control Surface is Moved by Two Hydraulic Cylinders

A

One From the Utility Hydraulic System and the Other From

the Flight Hydraulic System

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16
Q

Trim Button Causes Operation of ____ powered motor

A

AC

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17
Q

Cutout Switches Interrupt Horizontal Tail Trim When

A

Opposite Stick Force is Exerted

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18
Q

Rudder trim ____ degrees

A

2 degrees and Only Operable with SAS in YAW DAMPER

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19
Q

Rudder deflection Limiter

A
  • Nose Gear is ¾ or Less Extended, Rudder Deflection is Limited to 6 From Neutral in Either Direction
  • Nose Gear is More than ¾ Extended, Full Rudder Deflection of 30 From Neutral in Either Direction
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20
Q

Stability Augmenter System (SAS) power, turned on/off by, can you fly without?

A
  • AC powered
  • EGI switch on AAP
  • Yes, unless solo and formation
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21
Q

Flap motors are ____ power?

A

AC

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22
Q

If One Flap Motor Fails, Both Flaps are Actuated by?

A

Rotary Shaft but will take longer

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23
Q

Flap-Horizontal Tail Interconnect System (FLAP-SLAB)

A
  • Repositions Horizontal Tail to Eliminate Pitch Changes Caused by Flap Movement
  • Increased Horizontal Tail Deflection in Nose Down Direction When Flaps are Lowered
  • Increases the Amount of Horizontal Tail Deflection Per Inch of Stick Travel
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24
Q

Flaps Lever and Position Indicator

A
  • FCP Lever Actuates the Electrical Switch that Operates the Two Flap Motors
  • Position Indicator Operates on DC Power and Reflects Right Flap Position Only
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25
Q

Auxiliary Flap Control Switch

A
  • NORM – Provides Flap Settings of 0%, 60%, and 100%

- EMER – Provides Any Flap Setting Specified by the Flap Lever

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26
Q

Speed Brake System

A
  • DC controlled, hydraulically powered
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27
Q

Can RCP override FCP speed brake?

A

Yes, For FCP To Regain Control, Move Switch to OFF Then Back to Appropriate Position

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28
Q

“Why does the T-38C aircraft have two hydraulic reservoirs
A) to provide a reserve supply of hydraulic fluid
B) To allow for two independent hydraulic systems
C) So one system can supply fluid to the other if the other gets low”

A

B

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29
Q 
"Indicate whether the follow hydraulic components are powered by the flight control system, utility system, both, or another source
A) Speed Brake
B) Ailerons
C) Nosewheel steering
D) Landing Gear
E) Rudder
F) Stability Augmentor
G) Stabilizer
H) Wheel Brakes"
A 
"A-U
B-U,F
C-U
D-U
E-U,F
F-U
G-U,F
H-O"
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30
Q

Whate are the minimum, normal range, and maximum hydraulic system pressure limitations

A

1500, 2850-3200, 3200

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31
Q

“When will the hydraulic caution light illuminate
A) When the hydraulic pressure drops below 1500psi
B) When the hydraulic pressure drops below 1800psi
C) When the hydraulic pressure rises above 3200psi
D) When the hydraulic pressure is above or below normal operating range”

A

A) The hydraulic caution light illuminates when there is a hydraulic overtemp and hydraulic low pressure. It will NOT illuminate for an overpressure, but an overpressure will often lead to an overtemp

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32
Q

“Can you maneuver the T-38C with the left engine frozen and the right gearbox failed
A) Yes, but a controlled ejection is recommended if not at a low altitude
B) Yes, but a landing cannot be made
C) No, immediate ejection is recommended”

A

C) A frozen engine produces no hydraulic pressure along with a gear box fail. With no pressure, you get not control

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33
Q

“Which of the following statements about the airframe mounted gearbox are true
A) If the left hydraulic and left generator lights illuminate at the same time, this probably indicates gearbox failure
B) If only a generator light illuminates while advancing the throttle from idle to MIL, this probable indicates a gearbox failure
C) If the gearbox fails to shift, you lose hydraulic pressure and AC generator on that side
D) If the gearbox fails to shift, you lose the generator on that side only”

A

A D) When you lose the airframe mounted gearbox, you lose the generator and the hydraulic pump. A gearbox fail to shift does not affect the hydraulics on that side

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34
Q

“If the left airframe mounted gearbox shaft shears
A) windmilling RPM will provide normal utility hydraulic pressure
B) the UTILITY HYDRAULIC and MASTER CAUTION lights illuminate as pressure decreases below 1800psi
C) the gear must be lowered with the alternate system
D) Both A and C”

A

C) With a gearbox shaft shear, you lose the hydraulics on that side. Left side hydraulics control flight controls, NWS, speed brake, SAS and normal landing gear extension

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35
Q

With 0 hydraulic pressure will you have control of the primary flight controls

A

No

36
Q

The flight control hydarulic system is which side and controls what

A

Right, ailerons, rudder, horizontal stabilizer

37
Q

The utility hydraulic system is which side and controls what

A

Left, flight controls, landing gear, NWS, stability augmentor, speed brake

38
Q

With both hydraulic systems inop, can you move the flight controls

A

no

39
Q

What are the main components of each hydraulic system

A

reservoir, pump, indicating and warning system

40
Q

Where are the hydraulic reservoirs mounted

A

in the engine bay, above the hydraulic pumps

41
Q

How are the hydraulic reservoirs pressurized

A

bleed air from the engine

42
Q

The hydraulic pump is driven by what

A

by the engine through the airframe mounted gearbox

43
Q

How much hydraulic fluid is in the system

A

varies depending on requirements

44
Q

When the airfram mounted gearbox fails to shift, how does this affect the hydraulic system

A

No effect, the hydraulic pump compensates for both low and high engine speeds

45
Q

How is the hydraulic pressure indicating system powered

A

AC for each respective side

46
Q

After the MASTER CAUTION and the respective hydraulic light illuminte, when will both lights extinguish

A

When hydraulic pressure rises above 1800psi

47
Q

What distinguishes a hydraulic overtemp vs low pressure indications

A

Both will give MASTER CAUTION and respective hydraulic light but overtemp will indicate normal hydraulic pressure

48
Q

If caution light illuminate due to hydraulic overtemp, when will the lights extinguish

A

when the hydraulic temp drops below the high-temperature point (the temp at which the lights went on)

49
Q

Will a leak in one hydraulic system affect the other?

A

no

50
Q

With a leak in a hydraulic system, the hydraulic pressure ___ with control movements and eventually ___.

A

fluctuates wildly, drops to zero

51
Q

With Low hydraulic pressure avoid ___ and then ___

A

avoid zero and negative-G flight, land as soon as possible

52
Q

What can cause zero hydraulic pressure

A

engine seizure and airframe mounted gearbox failure

53
Q

With zero hydraulics, land as soon as ___

A

land as soon as possible

54
Q

What can cause high hydraulic pressure

A

faulty pressure regulator or a line restriction

55
Q

What can cause high hydraulic temp

A

continued operation at high hydraulic pressure, engine fire or hydraulic pump malfunction

56
Q

Continued operation with high hydraulic temp will affect the flight controls how

A

eventually flight controls will get sluggish and may bind

57
Q

Indication of airframe mounted gearbox failure

A

Both genertor and hydraulic light illumination on a side

58
Q

With a rudder system failure, the rudder may defelect a full __ degrees

A

30

59
Q

With a rudder system failure, the rudder will reach the full 30 degree position in __ to __ seconds

A

3-5

60
Q

Indications of rudder system failure

A

increasing yaw followed by a violent roll and departure from controlled flight

61
Q

Can the aircraft be controlled with a rudder system failure

A

only for the first two seconds, but the 30 degree deflection will lead to an accelerated stall and become completely uncontrollable

62
Q

If rudder system failure in flight occurs, what actions are taken

A

immediate ejection

63
Q

If rudder system failure is suspected on takeoff roll, what actions are taken

A

high speed abort or ejection

64
Q

What is the difference between Rudder system malfunction and flap and aileron malfunction

A

Aircraft is controllable with flap or aileron malfunction

65
Q

With a stability augmentor malfunction, the rudder can move a maximum of _ degrees in as little as _seconds

A

4, 0.25

66
Q

If in highspeed and high AOA a stability augmentor malfuntion can cause ___

A

an abrupt uncommanded roll

67
Q

If a stability augmentor malfuction occurs, what action is taken

A

turn the stab-aug system OFF

68
Q

If turning the stability augmentor system off due to a malfunction, can you continue your mission

A

yes

69
Q

If the yaw damper swith disengages in flight, can you turn it back on

A

yes

70
Q

if you reset the yaw damper and it immediately disengages but rudder response is normal, can you continue your mission

A

yes, but write it up

71
Q

Indications of rudder system failure vs a stability augmentor failure

A

with a stab-aug failure the rudder can still be moved and the aircraft is still easily controlled

72
Q

What three conditions cause the gear warning (HUD, red light, aural tone) to go off when the gear is up?

A

210 KCAS or less, 10,000 feet or below, both throttles below 96%

73
Q

When the gear handle is up, what does a red light in the handle indicate?

A

gear doors not up and locked

74
Q

When the gear handle is down, what does a red light in the handle indicate?

A

all three landing gear are not down and locked

75
Q

What electrical system operates the flaps?

A

Right AC

76
Q

How many right AC-powered flap motors are there?

A

2

77
Q

How are the flap levers interconnected and which one actuates the electrical switch?

A

Mechanically; front

78
Q

What stops the flaps at 60% when the lever is placed that position?

A

Sensing switch

79
Q

What stops the flaps at UP or FULL when the lever is placed that position?

A

limit switches

80
Q

How are the flaps connected to the slab?

A

Mechanically through a flexible cable in the right flap

81
Q

What are the 3 functions of the flap/slab interconnect?

A

Reduces pitch changes with flap actuation, increases nose-down stick authority, and increases amount of slab deflection per inch of stick travel (pitch sensitivity)

82
Q

Does the stick move as the flap/slab interconnect repositions the slab?

A

Nosewheel returns to center

83
Q

What will be the indications of a flap/slab interconnect failure with flaps down?

A

Sudden pitchup and stall

84
Q

What is the best course of action to land with flap/slab interconnect failure?

A

Land no-flap

85
Q

What intermediate flap setting should you use of a no-flap landing is not possible with flap/slab interconnect failure?

A

30-45%

86
Q

What does the aux flap control allow you to do?

A

Position flaps in intermediate positions

87
Q

How can you position flaps in intermediate positions using the aux flap switch?

A

60% becomes the OFF detent

T38C Systems (15 decks)

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