SY Flashcards
(127 cards)
1
Q
Three elements necessary for engine operation
A
Air, Fuel, Heat
2
Q
Two major sections that make up the engine
A
- Gas Generation Section
- Power Turbine Section
3
Q
Name the only primary component of the accessory compartment
A
The starter
4
Q
Describe the PT6A-68 engine
A
reverse-flow, free-turbine turboprop engine rated to produce 1100 shaft horsepower
5
Q
Name the gas generator section components
A
4C’s
1. Compressor inlet
2. Compressor
3. Combustion chamber
4. Compressor turbine
6
Q
Name the power turbine section
A
- Power Turbines
- Exhaust Case
- Reduction Gearbox
- Propeller Shaft
7
Q
Name the exhaust components
A
- Exhaust ports
- Exhaust stacks
8
Q
What do the exhaust stacks do?
A
- turn the exhaust air from the exhaust ports 180 degrees
- provide a small amount of additional thrust
9
Q
Name the ignition system components
A
- Ignition Exciter
- Two igniter cables
- Two igniters
10
Q
What positions are the igniters installed?
A
4 and 9 o’clock at the combustion chamber
11
Q
What provides the fuel for start?
A
The FMU (Fuel Management Unit)
12
Q
What provides air for start?
A
The Starter
13
Q
What provides heat for start?
A
The Ignition System
14
Q
Name the positions of the ignition switch
A
- ON
- NORM
15
Q
What illuminates when the igniters are activated?
A
Green IGN SEL annunciator
16
Q
What does the PCL control?
A
Engine fuel flow
17
Q
How are the forward and aft PCL’s connected?
A
A push-pull rod
18
Q
How is the PCL connected to the FMU?
A
Mechanically and Electrically (through PMU)
19
Q
Name the three labeled positions of the PCL
A
- MAX
- IDLE
- OFF
20
Q
Primary functions of the PMU
A
- Keep engine and prop within operating limits
- Processes power requests
- Determines available power
- Provides linear response between IDLE and MAX
21
Q
Amber PMU STATUS annunciator in flight, Master CAUTION, and aural tone
A
Indicates either failure of WOW switch or a WOW mismatch. PMU will not revert to ground mode after landing
22
Q
Amber PMU STATUS annunciator after landing
A
PMU fault picked up in flight, notify MX
23
Q
Red PMU FAIL annunciator, Master CAUTION and WARN, and aural tone
A
Non-functional PMU
24
Q
PMU Power Supply
A
Primary - PMA (Permanent Magnet Alternator) 32 VAC which PMU converts to DC
Alternate (PMA Fail) - 28 VDC from Battery Bus
25
Oil System Purpose
provide a steady flow of filtered oil to the engine bearings, reduction gears, accessory drives, and propeller.
26
Oil Scavenge system
several pressure and scavenge pumps after the bearings gears, drives, and prop which return oil to the oil tank.
27
Oil Cooler
Cools scavenged oil before returning to the oil tank
28
Chip Detector
located in the reduction gearbox, sense metallic fragments in the oil system
29
Red CHIP annunciator, Master WARN, and aural tone
Chip detector has detected metal fragments
30
How long do you have to CHECK oil after shutdown?
15-20 minutes
31
How long do you have to SERVICE oil after shutdown?
30 mins
32
Amber OIL PX annunciator
15 and 40 psi at IDLE
40 and 90 psi for 10 seconds above IDLE
33
Red OIL PX annunciator
15 psi or below at IDLE
40 psi or below above IDLE
34
Both the Red and Amber OIL PX annunciators
(Ops Limit)
Between 15 and 40 psi at IDLE for 5 seconds or more
35
Describe the purpose of the propeller
To convert power into thrust
36
What controls Np?
The PMU and PIU (Prop Interface Unit)
37
What RPM is 100% Np?
2000 RPM
38
At what altitude is 100% torque available?
12,000-16,000 MSL
39
Phase Shift Torque Probe
Located on the reduction gearbox. Measures Np. Signal monitored by PMU
40
Mechanical Overspeed Governor Max Np
106% Np, 2120 RPM
41
Three Pitch Conditions
1. Feathered
2. High Pitch (coarse)
3. Low Pitch (flat or fine)
42
PIU (prop interface unit) function
regulates system oil pressure to the pitch change mechanism
43
What does the prop do when oil pressure is lost?
Moves towards feather (wont fully feather until PCL is placed in off)
44
When starting the T-6A, the PCL should be
pushed forward until a green ST READY annunciator illuminates
45
Engine Data Manager (EDM)
computer unit located in the left avionics bay that monitors and processes engine operation data
46
EDM Engine Related Tasks
It drives the primary, alternate, and engine/systems displays and illuminates advisory, caution, or warning annunciators
47
EDM Non-Engine Related Tasks
fuel balancing, fuel quantity indications, activation of the nosewheel steering annunciator, a display of DC volts, DC amps, hydraulic pressure, cockpit pressure altitude, and cockpit pressure differential.
48
PEDD (Primary Engine Data Display)
Provides visual indication of primary engine data.
49
PEDD Display Information (5 indications)
1. Torque
2. ITT (Interstage Turbine Temp)
3. N1 (Gas Generator Speed)
4. Np (Propeller RPM)
5. IOAT (Indicated Outside Ambient Temp)
50
Torque
Resistance to rotation by the prop. Measured by phase-shift torque probe.
51
ITT (Interstage Turbine Temp)
Temp between compressor turbine and the power turbine measured at the combustion chamber.
52
N1 (Gas Generator Speed)
The speed pf the compressor turbine. Measured by magnetic pulse sensor on the accessory gearbox.
53
Np (Propeller RPM)
Prop speed measured by phase shift torque probe
54
IOAT (Indicated Outside Air Temp)
Measured by T-1 Sensor located in the inlet plenum.
55
AEDD (Alternate Engine Data Display)
provides each cockpit with a backup visual indication of engine operations. Data not processed by PMU (like PEDD), except Torque.
56
AEDD Display Info (7 indications)
1. RITT (Raw Interstage Turbine Temp)
2. Torque
3. N1
4. Cockpit Pressure Altitude
5. ΔP (Cockpit Differential Pressure)
6. Fuel Flow
7. Fuel quantity
57
Red CKPT PX annunciator, MASTER WARN, aural tone
ΔP exceeds 3.9 to 4.0 psi
58
Amber CKPT ALT annunciator, MASTER CAUTION, aural tone
Cockpit altitude exceeds 19,000 feet.
59
ESD (Engine Systems Display) Info (5 indications)
1. Oil Temperature
2. Oil Pressure
3. Hydraulic Pressure
4. DC Voltage
5. DC Amperage
60
Oil Temperature
Measured downstream of the main oil pump by a transducer
61
Oil Pressure
Measured downstream of the main oil pump by a transducer
62
Hydraulic Pressure
Measured by a pressure sensor located on the power pack reservoir
63
Hydraulic Pressure Normal Operating Range
2880-3120 PSI
64
Fire Warning System Components
1. Core Element
2. Sensor Tube
3. Responder Assembly
65
Fire Detection Core Element
Senses fires/hot gas
66
Fire Detector Sensor Tube
Senses average temps for overheat
67
Firewall Shutoff Handle shuts off supply of these 3 systems
1. Hydraulics (to engine)
2. Fuel (to engine)
3. Bleed Air (from engine)
68
#1 Fire Power Source
Batt Bus
69
#2 Fire Power Source
Gen Bus
70
PEDD Power Source
Gen Bus
71
AEDD Power Source
Gen and Batt Bus (redundant)
72
ESD Power Source
Gen Bus
73
Types of Abnormal Starts
Hot, Hung, No-Start
74
Hot Start Indications
High/Rapidly Rising ITT
Lower N1
Lower Np
75
Hung Start Indications
Slow Rising ITT
Lower N1
Lower Np
76
No-Start Indications
No ITT
Lower N1
No Np
No Torque
77
Name the electrical system components
starter/generator
battery
auxiliary battery
external power receptacle
78
Name the two buses in the electrical system
Battery Bus (left)
Generator Bus (right)
79
Starter/Generator
primary aircraft power source. provides 28 VDC power and is capable of supplying 300 amps
80
Generator Control Unit
monitors generator and trips off-line in the event of a malfunction/located in AFT right cockpit.
81
Generator Control Switch Operation
magnetically held and electrically interlocked
82
Avionics Master Switch
Power for all avionics and radio systems in both cockpits EXCEPTIONS:
1. UHF control unit
2. UHF transceiver
83
Bus Tie Switch
used to tie the battery and generator buses together.
2 Positions: OPEN and NORM
84
Secondary Power Components
(everything but the starter/gen)
1. 24VDC Battery
2. 24 VDC Auxiliary Battery
3. External Power Receptacle
85
Primary Battery
provides power for engine starts and is capable of powering all electrical systems (except air conditioning, which is automatically shed)
86
Battery Switch Operation
magnetically held and electrically interlocked
87
Auxiliary Battery
powers a minimum number of aircraft systems and avionics in the event of failure of the generator and primary battery
88
External Power Control
External power is distributed on the battery bus, and is controlled by the battery switch (BAT) on the right forward switch panel
89
Individual Avionics Lighting
EFIS, RMU, AOA, GPS Panels all have their own dimmer knob
90
Landing Light
Left Main Gear. Will not illuminate until down and locked.
91
Taxi Light
Right Main Gear. Will not illuminate until down and locked.
92
Anti-Collision Light Flash Rate
30 times per minute, synchronous
93
What does mass balancing do?
Regulate control pressures, prevent control flutter, and improve control stability
94
What is mass balancing?
Moving the center of gravity of the control surface to its hinge line
95
The TAD calculates inputs to rudder trim based on these 4 parameters
1. Pitch Rate
2. Altitude
3. Airspeed
4. Engine Torque
96
The primary hydraulic system operates the following:
Gear and inboard gear doors, flaps, speed brake, nosewheel steering
97
T-6A hydraulic system operating pressure
3000 +/- 120 PSI
98
What are the 5 selector valves included in the selector manifold?
Landing Gear, Gear Doors, Speed Brakes, Takeoff Flaps, and Landing Flaps
99
Amber HYDR FL LO light comes under when
Reservoir fluid drops below 1 quart
100
Three circumstances in which emergency hydro is operated
Primary Hydro Failure, Engine Failure, Batt Bus Failure
101
4 Major Canopy Components
Frame, Forward windscreen, Front Cockpit Transparency, Rear Cockpit Transparency
102
Forward Transparency/Windscreen Birdstrike Rating
4lbs/270 KIAS
103
4 Canopy Sub-Assemblies
Hinge/strut system, Locking/Latching System, Sealing System, Canopy Fracturing System (CFS)
104
How many hooks hold the canopy closed?
5
105
How many switches illuminate the Red CANOPY light on the CWS?
Four. 3 on the hooks, 1 on the sill
106
What is the source of air for the canopy pressure seal?
Engine bleed air from the anti-g system
107
Piezoelectric crystals
used to detonate explosive chords in CFS. Do not require electricity to work
108
Flexible Linear Shaped Chord (FLSC)
Mounted on forward transparency for more powerful explosion (thicker transparency)
109
Mild Detonation Chord
Mounted on rear transparency (less powerful due to thinner transparency)
110
When would the Manual Override Handle be used?
When in mountainous terrain and seat pilot separationis is desired above 14,000 MSL
111
Powered Inertia Retraction Device (PIRD)
Properly positons shoulders for ejection.
112
How well the ejection seat performs depends on these 3 factors
dive angle, bank angle, sink rate
113
How far behind the aft seat does front seat ejection take place?
.37 seconds
114
What is the function of the drogue chute?
stabilize the seat and aid in deceleration
115
At what altitude will the seat separate and chute deploy?
14,000-16,000 MSL
116
When does the personal locator beacon begin transmitting?
When the survival kit separates from the seat
116
When does the personal locator beacon begin transmitting?
When the survival kit separates from the seat
117
How long does it take to deploy the SSK?
4 seconds
118
Primary Flight Controls
Ailerons, Rudder, Elevator
119
Secondary Flight Controls
1. Aileron Trim
2. Elevator Trim
3. Rudder Trim
4. Trim Aid Device (TAD)
(All electro-mechanically operated)
120
Which cockpit has priority for roll/pitch/yaw trim?
Rear Cockpit
121
What pressure does the reservoir step down piston regulate pump return pressure to?
50 PSI
122
What pressure doe the pressure release valve actuate?
3250-3500 PSI
123
What is the purpose of the hydraulic Slide Valve #1?
Isolate the hydro pressure coming from the engine driven pump once the Emergency System has been activated
124
3 specific scenarios where emergency extension is required
engine failure, batt bus failure and primary hydro system failure
125
When does the EHYD PX LO light come on?
2400 +/- 150 PSI
126
When will the hydraulic fuse trip on the emergency hydraulic system?
.25 GPM or about 1 pint of fluid lost
