SYSTEMS Flashcards
1
Q
ELECTRICAL
If the amber BATTERY CHG annunciator illuminates in flight, what initial action does the checklist say to do?
A
Turn the battery switch OFF
2
Q
ELECTRICAL
If the BATTERY CHG light does not extinguish in flight when the battery control switch is placed to OFF, what action should be taken?
A
Land at nearest suitable airport
3
Q
ELECTRICAL
Why should the BATT switch be left on during use of external power?
A
To protect against voltage spikes
4
Q
ELECTRICAL
How is the battery cooled?
A
How is the battery cooled?
Air-cooled through a thermostatically controlled valve installed at the air inlet tube adjacent to the battery drain.
5
Q
ELECTRICAL
Where is the battery located?
A
In the right wing center section
6
Q
ELECTRICAL
What is the rating for the battery?
A
24-volt, 34/36 ampere-hour
7
Q
ELECTRICAL
What are 3 functions of the GEN CONTROL UNIT?
A
- Links isolation bus with generator busses.
- Acts as a fuse. Once failed, must be replaced.
- Provides isolation of the GEN in the event of a GEN bus fault.
8
Q
ELECTRICAL
What indication is provided to alert the operator that an external power plug is connected to the airplane?
A
An EXT PWR light
9
Q
ELECTRICAL
To protect the battery from damage, the external power voltage must not go over what value for more than two minutes?
A
30 volts
10
Q
ELECTRICAL
How much continuous current should the external power unit be capable of supplying?
A
300 amperes
11
Q
ELECTRICAL SYSTEMS
Where is the external power connector located?
A
Under the right wing, outboard of the engine nacelle
12
Q
ELECTRICAL
What is the minimum required battery voltage before using an external power unit?
A
20 volts
13
Q
ELECTRICAL
GEN CONTROL UNIT
What are the 6 functions of the GEN CONTROL UNIT?
A
What are the 6 functions of the GEN CONTROL UNIT?
- GEN paralleling
- Line contactor relay control
- Over Excitation Protection
- Overvoltage protection
- Reverse current sensing / control
- Voltage regulation
14
Q
ELECTRICAL
When a generator is off line, what indication is present?
A
An amber DC GEN light is on
15
Q
SYSTEMS ELECTRICAL
When an engine is being started, in what position should its GEN switch be?
A
OFF
16
Q
ELECTRICAL
How is a generator turned on?
A
Hold switch to RESET for 1 sec and release to ON
17
Q
ELECTRICAL
What is the individual generator rating?
A
28-volt, 250-ampere
18
Q
ELECTRICAL
Where are the generator switches located?
A
Under a gang bar on the pilot’s left subpanel
19
Q
ELECTRICAL
Which items are on the Hot Batt Bus?
A
Which items are on the Hot Batt Bus?
- BATT Relay
- Clocks
- Ext entry / Threshold lights
- EXT PWR Sensing
- Firewall Shutoff Valves
20
Q
ELECTRICAL
What is the rating of each inverter?
A
115-volt and 26-volt, 400 Hz
21
Q
ELECTRICAL
Where is the INVERTER switch located?
A
On the pilot’s left subpanel
22
Q
ELECTRICAL
How many inverters are there?
A
2
23
Q
ELECTRICAL
After starting the right engine and turning the right generator on, what should the load meter reading decrease to before starting the left engine?
A
50% (.50 )
24
Q
ELECTRICAL
To protect the battery from damage, the external power voltage must not go over what value for more than two minutes?
A
30 volts
25
FIRE DETECTION
## Footnote
What does a "L ENG FIRE" (ILLUM) light on the Master Caution Warning Panel indicate?
Fire in Left Engine Compartment
26
FUEL SYSTEM
Fuel is heated prior to entering the fuel control unit by:
Engine oil, through an oil-to-fuel heat exchanger
27
FUEL SYSTEM
When is cross-feed use authorized?
For single-engine operation
28
FUEL SYSTEM
Which of the following is not affected when the cross-feed switch is moved to the right or left?
auxiliary fuel transfer override function
29
FUEL SYSTEM
Which of the fuel pumps is electrically powered?
Standby boost pump
30
FUEL SYSTEM
The fuel panel check tests electrical continuity to which items?
* Standby boost pumps
* Cross-feed valve
* Firewall Shutoff Valves
31
FUEL SYSTEM
Operation of the engine with the FUEL PRESS light illuminated is limited to:
10 hours - main engine fuel pump overhaul or replacement.
32
FUEL SYSTEM
Which limitations applies to operation with aviation gas?
* Max FL200 with 1 standby pump inop
* 150 hours between overhauls
33
**FUEL**
Name the 4 fuel pumps
Name the 4 fuel pumps
1. Engine driven pump - accessory case prior to FCU.
2. Engine driven boost pump
3. Electric standby boost pump
4. Transfer jet pump.
34
**FUEL**
Fuel System Description
Fuel System Description
* Separate fuel system each engine
* Main and Auxiliary system
* Each system - 4 fuel pumps
* Main - nacelle / 5 interconnected tanks
* Fuel supplied to engine from nacelle tank
* AUX - 1 tank located between nacelle / fuselage
* Transfer pump transfers fuel from the AUX tank
35
FUEL SYSTEM
Which of the following is a function of the electric standby boost pump?
* Primary boost pump failure
* Aviation gas - \> FL200
* X-feed operation
36
GENERAL
What is the width of gear?
17' 2"
37
GENERAL
What is the length from nose to tail
43' 10"
38
GENERAL
Total Oil capacity?
14.2 gal
39
GENERAL
Oil operating range?
Full - 4.0 Qts LOW
40
GENERAL
What is the hight to top of tail?
14' 10"
41
GENERAL
What is the outside turning radius?
39' 10"
42
GENERAL
What is the length from wingtip to wingtip?
54' 6"
43
LIGHTING
What bus powers the air stair floodlight?
Hot battery bus
44
LIGHTING
Where is the baggage-area light switch located?
Just inside and aft of the air stair doorframe
45
LIGHTING
Where are the majority of cockpit lighting controls?
Overhead panel
46
LIGHTING
Where are the ice lights mounted?
On the outside of the engine nacelles
47
LIGHTING
What is the switch labeled MASTER PANEL LIGHTS used for?
To control power for all cockpit panel lights
48
LIGHTING
Where are the recognition lights mounted?
On the vertical stabilizer
49
LIGHTING
How are the threshold and aisle lights turned on?
Automatically, when the air-stair door is opened and the threshold switch turned on
50
LIGHTS
Where is the baggage-area light switch located?
Just inside and aft of the air stair doorframe
51
LIGHTS
Where are the majority of cockpit lighting controls?
Overhead panel
52
LIMITATIONS
What are the starter limits?
40 seconds ON, 60 seconds OFF
40 seconds ON, 60 seconds OFF
40 seconds ON, 30 minutes OFF
53
MASTER WARNING SYSTEM
How can the annunciator lights be tested?
With the PRESS TO TEST switch
54
MASTER WARNING SYSTEM
When will a red annunciator light extinguish?
When the indicated fault is cleared
55
MASTER WARNING SYSTEM
To illuminate the CAUT LGND OFF light on 200 models, what action must be taken?
Move the CAUTION switch to OFF
56
MASTER WARNING SYSTEM
To extinguish a MASTER WARNING flasher, what action must be taken?
Depress either MASTER WARNING flasher
57
MASTER WARNING SYSTEM
How are the MASTER CAUTION flashers dimmed?
Automatically relative to cockpit light intensity
58
**PNEUMATIC**
Name the items on the Vacuum / Pneumatic system:
Name the 8 items on the Vacuum / Pneumatic system:
1. Deice Boots
2. Bleed Air Warning
3. Hobbs Meter
4. Brake Deice
5. LDG Gear Hyd Res
6. Pressurization Controller
7. Door Seal
8. Outflow and Safety Valves
59
POWERPLANT
During a ground start of the right engine, the IGNITION ON light should illuminate:
When the start switch is moved to the IGNITION and ENGINE START position.
60
POWERPLANT
After lift-off, if an auto-feather is initiated, the immediate requirement is to:
Continue and allow propeller to feather and stop.
61
POWERPLANT
When the AUTO-IGNITION switch is in the ARM position, ignition is:
Inactive but armed if torque is \> 400 foot-lbs.
62
POWERPLANT
If a chip detector light illuminates, you must:
Check engine instruments
* Normal - no action required
* Otherwise shut the engine down
* Land as soon as practical.
63
POWERPLANT
Which of the following is the most accurate definition of Engine Torque Readout?
Power delivered to the propeller
64
POWERPLANT
During ground operation at LO IDLE, you note that ITT is exceeding 750°C.
What should be done to reduce ITT?
* Reduce accessory load or
* Increase N1 rpm
65
POWERPLANT
## Footnote
When using maximum reverse power at HI IDLE and full increase RPM, you would expect a maximum propeller rpm of:
1,900
66
POWERPLANT
The PT6A engine power section consists of:
A two-stage reaction turbine.
67
POWERPLANT
The function of the reduction gear system is to provide gear reduction:
For the propeller
68
When does the rubber seal around the air stair door begin to inflate?
When weight is off the landing gear.
69
What is the purpose of an inverter?
* Convert DC power to AC power.
* #1 Inverter receives power from Left GEN Bus
* #2 Inverter receives power from Right GEN BUs.
* Produce 115 V AC and 26 V AC power.
70
What happens when the BATT switch is turned on?
Battery relay closes connecting the battery to the main battery bus and to the starter relay.
71
When will the CHARGE annunciator illuminate?
A charge rate of greater than 7 amps for 6 seconds.
72
Line Contactor Relay Control
* When gen output is acceptable for system use, GCU closes the relay allowing GEN to power the elect sys.
* GCU also monitors operation of the GEN and opens the line contactor relay if a fault should occur requiring isolation of the GEN from the ELEC SYS.
73
VOLTAGE REGULATION
* GCU monitors GEN output voltage and controls shunt field excitation in the GEN to maintain constant voltage.
* Maintains GEN output at 28.25 +/- .25v.
74
GENERATOR PARALLELING
* GCU has built in circuitry to maintain the GEN elec loads to within 10% of each other.
75
OVER EXCITATION PROTECTION
* If starter-GEn fault is such that voltage increases without control but does not go in to overvoltage, over excitation protection is activated.
* If a failure creates excessive field excitation, the affected or faulty GEN will attempt to carry aircraft's entire elec load. The affected GEN is isolated from the sys.
76
What is the purpose of the Current Limiters?
* Link isolation bus with the GEN busses.
77
What is located on the RH GEN Bus
* Landing gear motor
* Copilot's Windshield Heat
* Aft Blower
* AFT Elec Heat
* Air Conditioner Clutch
* Vent Blower
* Toilet
* Inverter (Cabin Outlets)
* Avionics Bus #2
* Inverter Control #2
* Inverter #2
* DC Test Jack
78
**What is located on the LH GEN Bus**
* Pilot's Windshield Heat
* Condensor Blower
* FWD Elec Heat
* Avionics Bus #1
* Avionics Bus #3
* Inverter #1
79
How is the nacelle tank fed?
* Gravity feed from the interconnected tanks in the wing.
* Jet transfer pump from the AUX tank.
80
How are the fuel tanks vented?
Through a recessed ram vent that is coupled to a protruding heated ram vent on the underside of the wing.
81
What is the function of the engine driven pump?
* Increases the fuel pressure producing an adequate spray pattern from the fuel nozzles into the combustion chamber.
* Must be operative for the engine to operate.
82
What is the function of the engine driven boost pump?
* Delivers low pressure (25-30 psi) fuel to the engine fuel pump to prevent cavitation.
* Operates when the gas generator (N1) is turning and provides sufficient fuel for start, takeoff, all flight conditions (except Avgas
83
What is the function of the Elec Driven STBY boost pump?
* Backup in the event an engine driven boost pump failure.
* Located in bottom of each nacelle tank
* Used for all X-feed operations.
* Used for Avgas
*
84
What is the function of the Jet Transfer pump?
* Transfers fuel from the AUX tank to the nacelle tank.
* Operates by venturi principle from motive flow.
* Actuated by switch on the fuel control panel.
* Switch placed in AUTO or manual AUX XFR OVERRIDE position.
85
How many fuel drains are located in each wing?
6
86
What items are on the accessory section?
* Oil Scavenge pumps
* Engine driven fuel pump
* Engine driven boost pump
* Starter generator
* Air conditioner compressor
87
What is the purpose of the Torque Limiter?
* Limits torque.
* Monitors torque of the reduction gear box
* Bleeds off P air which changes pneumatic servo pressure in FCU to reduce metered fuel flow.
* As metered fuel flow is reduced, the gas GEN speed reduces and thus reduces torque to preset limit of torque limiter.
* Protects the nose gear box and reduction gears from excess torque.
*
88
Explain the primary governor
* Control linkages operate the speeder spring to reposition the pilot vale to change prop RPM.
* Normal governing range is 1600-2000 RPM.
* Moving the prop lever into FEATHER will lift the pilot valve up.
* Oil is drained from the prop hub allowing the prop feathering spring and counter weights to feather the prop.
89
CONDITION LEVERS
* 3 Positions
* FUEL CUTOFF - fuel supply is stopped at FCU
* LOW IDLE - N1 56%
* HIGH IDLE - N1 70%. Provides more airflow through engine for better cooling, and more power for higher gen loads.
90
TORQUE METERS
Indicate how many foot-pounds of torque are being applied tot he prop shaft.
Generated from a torquemeter oil pressure converted to an electrical signal by the torque transmitter.
91
PROPELLER
* Blade pitch angle - changed by allowing engine oil to press against a piston moving the blades from a high angle (feathered) to a low angle (flat.)
* Primary governor controls the prop speed by using engine oil pressure to vary pitch of the prop blades.
* Overspeed governor and fuel-topping governors back up the primary gov.
* Fuel-topping governor - limits speed in reverse to a level preventing primary governor from becoming operational.
92
ELECTRICAL
## Footnote
What is the primary load of the main BATT BUS?
* Provides power to L/R GENS during start
* Powers the ISOLATION BUS
93
ELECTRICAL
What is the purpose of the isolation bus?
* Serves as a connection between the L & R GEN BUSSES
