SY1115-6 Flight Contorl and Hyfdraulics Flashcards
1
Q
How many hydraulic systems?
A
2 systems driven by respective engine driven hydraulic pump
2
Q
Is the reservoirs pressurized?
A
Yes, by 8th stage of compressor to prevent foaming
3
Q
What powers the hydraulic system pressure
A
airframe mounted gearbos
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
5
Q
Is there any interchange under norm ops
A
No, only if one system fails
-35 Minutes If Either System Reads 0 PSI
6
Q
Pressure Indicators and Caution Lights are ______to Each System
A
independent
7
Q
Flight Control Hydraulics power
A
Flight Controls
8
Q
Utility Hydraulics power
A
- Flight Controls
- Augmentation (SAS)
- Nose Wheel Steering
- Gear Extension/Retraction
- Speed Brake
9
Q
Pressure Indicators powered by
A
AC
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
11
Q
Shift Mechanism Maintains AC Output Between ______ cycles per sec
A
320 and 480 Cycles Per Second
12
Q
Gearbox Shift Occurs Between
A
65%-75%
13
Q
With one system at zero psi
A
Limits Flight Time to 35 Minutes
14
Q
Conventional Aerodynamic Feel in the Control Stick is Provided Artificially
A
Springs and Bob Weights
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
16
Q
Trim Button Causes Operation of ____ powered motor
A
AC
17
Q
Cutout Switches Interrupt Horizontal Tail Trim When
A
Opposite Stick Force is Exerted
18
Q
Rudder trim ____ degrees
A
2 degrees and Only Operable with SAS in YAW DAMPER
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
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
21
Q
Flap motors are ____ power?
A
AC
22
Q
If One Flap Motor Fails, Both Flaps are Actuated by?
A
Rotary Shaft but will take longer
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
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
25
Auxiliary Flap Control Switch
- NORM – Provides Flap Settings of 0%, 60%, and 100%
| - EMER – Provides Any Flap Setting Specified by the Flap Lever
26
Speed Brake System
- DC controlled, hydraulically powered
27
Can RCP override FCP speed brake?
Yes, For FCP To Regain Control, Move Switch to OFF Then Back to Appropriate Position
28
"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"
B
29
```
"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-U
B-U,F
C-U
D-U
E-U,F
F-U
G-U,F
H-O"
```
30
Whate are the minimum, normal range, and maximum hydraulic system pressure limitations
1500, 2850-3200, 3200
31
"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) 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
32
"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"
C) A frozen engine produces no hydraulic pressure along with a gear box fail. With no pressure, you get not control
33
"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 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
34
"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"
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
35
With 0 hydraulic pressure will you have control of the primary flight controls
No
36
The flight control hydarulic system is which side and controls what
Right, ailerons, rudder, horizontal stabilizer
37
The utility hydraulic system is which side and controls what
Left, flight controls, landing gear, NWS, stability augmentor, speed brake
38
With both hydraulic systems inop, can you move the flight controls
no
39
What are the main components of each hydraulic system
reservoir, pump, indicating and warning system
40
Where are the hydraulic reservoirs mounted
in the engine bay, above the hydraulic pumps
41
How are the hydraulic reservoirs pressurized
bleed air from the engine
42
The hydraulic pump is driven by what
by the engine through the airframe mounted gearbox
43
How much hydraulic fluid is in the system
varies depending on requirements
44
When the airfram mounted gearbox fails to shift, how does this affect the hydraulic system
No effect, the hydraulic pump compensates for both low and high engine speeds
45
How is the hydraulic pressure indicating system powered
AC for each respective side
46
After the MASTER CAUTION and the respective hydraulic light illuminte, when will both lights extinguish
When hydraulic pressure rises above 1800psi
47
What distinguishes a hydraulic overtemp vs low pressure indications
Both will give MASTER CAUTION and respective hydraulic light but overtemp will indicate normal hydraulic pressure
48
If caution light illuminate due to hydraulic overtemp, when will the lights extinguish
when the hydraulic temp drops below the high-temperature point (the temp at which the lights went on)
49
Will a leak in one hydraulic system affect the other?
no
50
With a leak in a hydraulic system, the hydraulic pressure ___ with control movements and eventually ___.
fluctuates wildly, drops to zero
51
With Low hydraulic pressure avoid ___ and then ___
avoid zero and negative-G flight, land as soon as possible
52
What can cause zero hydraulic pressure
engine seizure and airframe mounted gearbox failure
53
With zero hydraulics, land as soon as ___
land as soon as possible
54
What can cause high hydraulic pressure
faulty pressure regulator or a line restriction
55
What can cause high hydraulic temp
continued operation at high hydraulic pressure, engine fire or hydraulic pump malfunction
56
Continued operation with high hydraulic temp will affect the flight controls how
eventually flight controls will get sluggish and may bind
57
Indication of airframe mounted gearbox failure
Both genertor and hydraulic light illumination on a side
58
With a rudder system failure, the rudder may defelect a full __ degrees
30
59
With a rudder system failure, the rudder will reach the full 30 degree position in __ to __ seconds
3-5
60
Indications of rudder system failure
increasing yaw followed by a violent roll and departure from controlled flight
61
Can the aircraft be controlled with a rudder system failure
only for the first two seconds, but the 30 degree deflection will lead to an accelerated stall and become completely uncontrollable
62
If rudder system failure in flight occurs, what actions are taken
immediate ejection
63
If rudder system failure is suspected on takeoff roll, what actions are taken
high speed abort or ejection
64
What is the difference between Rudder system malfunction and flap and aileron malfunction
Aircraft is controllable with flap or aileron malfunction
65
With a stability augmentor malfunction, the rudder can move a maximum of _ degrees in as little as _seconds
4, 0.25
66
If in highspeed and high AOA a stability augmentor malfuntion can cause ___
an abrupt uncommanded roll
67
If a stability augmentor malfuction occurs, what action is taken
turn the stab-aug system OFF
68
If turning the stability augmentor system off due to a malfunction, can you continue your mission
yes
69
If the yaw damper swith disengages in flight, can you turn it back on
yes
70
if you reset the yaw damper and it immediately disengages but rudder response is normal, can you continue your mission
yes, but write it up
71
Indications of rudder system failure vs a stability augmentor failure
with a stab-aug failure the rudder can still be moved and the aircraft is still easily controlled
72
What three conditions cause the gear warning (HUD, red light, aural tone) to go off when the gear is up?
210 KCAS or less, 10,000 feet or below, both throttles below 96%
73
When the gear handle is up, what does a red light in the handle indicate?
gear doors not up and locked
74
When the gear handle is down, what does a red light in the handle indicate?
all three landing gear are not down and locked
75
What electrical system operates the flaps?
Right AC
76
How many right AC-powered flap motors are there?
2
77
How are the flap levers interconnected and which one actuates the electrical switch?
Mechanically; front
78
What stops the flaps at 60% when the lever is placed that position?
Sensing switch
79
What stops the flaps at UP or FULL when the lever is placed that position?
limit switches
80
How are the flaps connected to the slab?
Mechanically through a flexible cable in the right flap
81
What are the 3 functions of the flap/slab interconnect?
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
Does the stick move as the flap/slab interconnect repositions the slab?
Nosewheel returns to center
83
What will be the indications of a flap/slab interconnect failure with flaps down?
Sudden pitchup and stall
84
What is the best course of action to land with flap/slab interconnect failure?
Land no-flap
85
What intermediate flap setting should you use of a no-flap landing is not possible with flap/slab interconnect failure?
30-45%
86
What does the aux flap control allow you to do?
Position flaps in intermediate positions
87
How can you position flaps in intermediate positions using the aux flap switch?
60% becomes the OFF detent
