Pilot Training Manual Book Questions Flashcards
The EMB 120 is certified under:
Part 25
The EMB 120 has how many generators?
5
The EMB 120 forward entry door my be:
Raided and lowered manually
Raised hydraulically—lowered manually
The EMB 120 DV windows may be removed by the crew? T/F
True
If the main entry door is not securely closed and locked:
A door open light will illuminate in the cockpit
How many cycles can the forward entry door be operated without recharging its accumulator?
4
The EMB 120 has how many landing lights?
2
The EMB 120 has how many taxi lights?
2
Passenger cabin lighting is controlled by:
A 3 position switch located on the attendants panel
Taxi lights turn off automatically on landing gear retraction? T/F
True
The flight attendant my be called from:
The cockpit
The cabin
The lav
The emergency lights come on if:
The cockpit switch is in ARM and the EDC bus 1 fails
The cockpit switch is placed to ON
The attendants switch us placed to ON, regardless of the position of the cockpit switch
What warning systems does the EMB 120 have?
Visual
Aural
Vocal
The color of the alarm/indication system lights are:
Red and green
Amber and white
Visual alarm light dim levels are controlled automatically? T/F
False
How many power sources does the multiple alarm panel have?
2
Does the crew how the ability to lower the volume of the aural warning system?
No
The total usable fuel capacity is:
5732 pounds
The fuel system consists of what kinds of fuel pumps and how many of each?
4 Electric boost pumps
4 Scavenger jet pumps
2 Main jet pumps
The firewall shutoff valve is operated through the:
Fire extinguisher T-handle
What color light indicates crossfeed operation
White
When pressure fueling, the airplane must be electrically powered? T/F
False
APU fuel used goes through the fuel totalizer? T/F
True
What happens when fuel flow indicators loose power?
Digital indication goes blank
The APU provides a source of
Pneumatic and electrical power
Can the APU receive fuel from the left fuel tank?
Yes
The APU will automatically shutdown if rotating parts exceed
110%
During the APU start cycle, what commands starter disengagement?
ECU
Can the APU be operated in flight?
Yes
What engines does the EMB 120 have?
Pratt-Whitney 118 A/B
The engine has how many compressors?
2
The engine has how many turbines?
4
The engine power control is accomplished by the operation of
A combination of the EEC and the HMU
The device that provides essential fuel control functions in the absence of electrical power is
Hydromechanical metering unit (HMU)
The maximum torque allowed is
110% for 5 min
The EEC is normally used in what positions?
TO or ON positions
If the EEC light on the glareshield illuminates, this indicates
An electrical failure exists in the system
Which turbine provides power to the propeller shaft?
Power turbine
Maximum continuous torque
100%
Maximum continuous engine RPM
100%
Minimum oil temp for takeoff
45C
Oil pressure alarm light illuminates at
40 PSID
Condition lever positions are
MAX RPM
MIN RPM
FEATHER
FUEL CUT-OFF
The PW118 combustion section is defined as
Reverse flow annular combusor
Power lever movement provides direct control to
HMU
During engine start, with the ignition system set to AUTO
The igniters come on automatically
The igniters go off automatically
What if any indication does the pilot have to indicate that the engine igniters are energized
A white ignition light on the start/ignition panel will illuminate
After initiation the start cycle is automatically interrupted at approximately
50% Nh
How is the fuel heated
Engine oil
How many compressor bleed ports does each engine have?
2
How is fuel flow to the engine metered?
HMU/EEC
Failed fixed is a function of
The EEC
When does the EEC control function activate?
25% Nh
If the gust lock is set, power levers are restricted in movement? T/F
True
The condition lever has free movement from feather to fuel cut-off? T/F
False
Engine compressors are axial or centrifugal?
Centrifugal
The free power turbine is
A two stage axial flow
What are the engine bleed ports called?
P 2.5
P 3
Who makes the propeller
Hamilton-sundstrand
I’m normal operation, maximum governed propeller speed is
1300 - 1309 rpm
Normal operational pitch range is
79.2 (feather) to -15 (reverse)
In flight, Np is controlled by
PCU and condition lever
The main component for selecting propeller pitch is
PCU
The main component for changing propeller pitch is
Propeller servomechanism
If through a malfunction the propeller become fixed pitch, what items control Np
Power and speed changes
During taxi and reverse, which unit controls Np?
EEC
Pitch lock is term used to describe
A device which lock the propeller pitch in flight of the propeller oil pressure is lost
Which controls input sets the propeller speed
Condition lever
When operating in the beta range
The speed governor system has no control of propeller pitch
The beta valve position is adjusted by the
Power lever
Propeller blade angle at flight idle
17.6
In flight, if the engine has failed and propeller has not been feathered, it will then automatically feather? T/F
False
If an approach with autofeather armed and engine fail, with its propeller autofeather
No
Propeller syncs us activated by
System selected on and Np > 80%
The main purpose of the least selector value is to
Select the proper speed governor
(Normal or overspeed)
Engine bleed air is ducted from 3 separate ports? T/F
False
The duct leak warning system is activated when temperature is the duct region reaches
195* F
If a “duct leak” is detected, the bleed-air system will automatically shut off? T/F
False
If a “bleed overheat” is detected, the bleed-air system will automatically shut off? T/F
False
What prevents moisture from entering tubing or Deicers
A water separator system
Deicer boots are operated by pneumatic air flowing through
4 ejector flow control valves
Leading edge deicer boots are controlled by
2 timers
The modes of leading edge deicing are
On or off
Deice boots are inflated for a maximum of
6 seconds
When the leading edge system is selected the system cycles every
60 seconds
Angel-of-attack and slip-skid sensors are deiced by
Electric heat
Propeller deice is accomplished by
Electrical heat
The propeller deice system is protected from damage during ground operation by
Low oil pressure switch
When the “cold” mode of propeller deice is used the propeller blades are heated for
20 seconds
The recommended temperature for selecting “cold” mode operation is
Below -10* C
The windshield heat system heats the windshield to approximately
40-45* C
Should any segment of the anti-ice/deice system fail, the pilot would be alerted by a
Amber light
Static ports are electrically anti-iced? T/F
True
Windshield wipers move at a rate if _____ on high mode
140 strokes/minute
The EMB 120 is air conditioned by
Environmental control packs
On the ground an air conditioner malfunction (PACK FAIL) would probably be caused by
Failure of the ground cooling fan
Should there be a PACK FAIL malfunction, the system may be restarted by
Turning the pack control selector OFF then on
The conditioned air temperature is controlled by
The mixture of cold air from the turbine and bleed air
Temperature can be read from both the cockpit and the cabin? T/F
True
To increase air flow to the cabin, the system has
2 recirculation fans
With air conditioning system in the AUTO mode, the temperature range can controlled within
60* - 90* F
The manual mode of operation can be used at the pilots discretion? T/F
False
Should the air conditioning system malfunction and cause a DUCT OVERHEAT, the pilot will be warned by a
Amber light
The DUCT OVERHEAT light comes on when the internal temp reaches
245* F
The air distribution ratio between cockpit and cabin is
40-60
Gasped fans should not be used in the MIX position during flight
It may blow warm air on the passengers head
The airplane pressurized by mean of
Conditioned air from air-conditioning system
Pressurization is controlled in
Automatic mode and manual mode
Is the avionics compartment pressurized?
No
The maximum pressurization differential is
7.2 psid
How many outflows valves control air discharge?
2
In the AUTO mode, which valves are operational
Electropneumatic outflow valve
On the ground, engines running, electrical power on, power levers at GND IDLE, which pneumatic valves are open
Both, pneumatic and electropneumatic
The AUTO mode of setting pressurization is Alway used unless
The AUTO system fails
In manual mode, which valves are operational?
Pneumatic outflow valve
The cabin warning light comes on at
10,000 ft
With the engines and electrical system off which outflow valves are open
Both
The absolute cabin altitude limit is
13,000 ft
The cabin climb rate may be set between
200 - 1500 fpm
The cabin decent rate is may be set between
150 - 1000
During decent, if the controller is set as recommended the cabin should descend at
450 fpm
Upon landing does the the cabin automatically depressurize?
Yes
Does the EMB 120 have 2 independent hydraulic systems
Yes
How are the hydraulic systems identified
Green and blue
Hydraulic pressure is provided by
Engine-driven pumps
Hydraulic fluid may be blocked from flowing through the main hydraulic pump by
Pulling the engine fire T-handle
Are the hydraulic system basically identical
Yes
Which ways can the landing gear be extended
Gear handle
Alternate electrical system
Free-fall system
Position status of the landing gear is provided by
Proximity switches
The landing gear system is powered by which hydraulic system
Green
If the free fall emergency method of lowering the gear is necessary what unlocks the unlocks
Mechanical cables
How many landing gear positions indications are there
2
What will cause the gear warning system to sound off
Flaps selected beyond 17* with gear up
Power lever angle reduced below 66* with gear up
Airplane descends below 200 agl
Airplane descends below 1500 agl
Hydraulic pressure to the brake system is
3000 psi
Does the EMB 120 have antiskid feature
Yes
When the parking break is applied how many brakes are actuated
4
If during takeoff the pilot forgot to release the parking break
A voice message will warn the pilot
Are breaks automatically applied when landing gear is raised
Yes
Does the nose wheel have its own brake system
No
How many indications does the pilot have to warm him that the emergency/parking break is on
2
Can the anti skid system be turned on or off
Yes
The nose wheel steering is operated
Hydraulically through the green hydraulic system
Is the nosewheel steered by rudder pedals and the tiller
Yes
If the pilot sees the PRDAL STEER INOP warning light, what does this indicate
The nose wheel is not centered
The nose wheel may be steered through a ____ degree arc with the tiller
100*
Rudder pedals control nose wheel steering through a _____ degree arc
14 *
The EMB 120 has ____ rudders
2
The rudder system may be actuated by
Both green and blue hydraulic systems
Mechanically by push rode
Can the rudder system be turned on and off
Yes
If airspeed is above 120 knots and both hydraulic systems remain connected to the rudder what cockpit indication will the pilot see
OVERBOOST light
Does the gust lock hold the rudder in place
No
Rudder trim is a function of
Hydraulics
Ailerons are actuated by means of
A cable and rod assembly
Can the left and right ailerons may be operated independently by disconnecting one from the other in case of a stuck or jammed aileron
Yes
If the left aileron is jammed and the the system is disconnected can the aircraft be controlled with the autopilot
No
The autopilot servo is connected to
The left aileron actuator
With the disconnect system actuated the copilots control wheel operates
The right aileron
The elevator is actuated by means of
A cable and rod assembly
If the the elevator disconnect system was actuated and only the pilot sides was free, would the stall warning system still be completely operational
No
What axis of trim is available
Roll
Pitch
Yaw
The aircraft is equipped with ____ flap panels per wing
3
Flaps are actuated by
A hydraulic assembly
Flap setting positions are
0 -15
15 - 25
25 - 45
Which hydraulic system is the outboard flakes actuated by
Blue
An asymmetrical flap condition occurs when
Two flap panels in the same pare differ in position by more then 7*
A flap disagreement condition occurs when
2 pair of flaps differ by more then 7*
What method or indication does the pilot have to determine a flap position malfunction
View the flap annunciator panel
The EMB 120 has ____ independent pitot static systems
3
The mode C input for the ATC transponder comes from
Pilots encoding altimeter
The altitude alerted system visual and aural warnings triggers when
The aircraft is 400 feet from selected altitude
The aircraft deviates approximately 200 feet from selected altitude
Does the EMB 120 have 2 identical and independent AHRS
Yes
The auto flight system consists of
2 flight director systems
2 autopilots
Will the electric pitch trim switch on the control wheel disengage the autopilot
Yes
Will the vertical trim switch on the autopilot control panel disengage the autopilot
No
The electronics bay ventilation system
Had 2 internal recirculation fans that come in when temps exceed 80* F
The EMB 120 electrical system supplies
28 VDV and 26/115 VAC
The EMB 120 has how many generators
5
The EMB has how many batteries
2
When using external power, can the APU generator be used
No
The EMB 120 main battery rating is
24 volt
36 AH
The main generator ratings are
28VDC
400 amps
During the start phase, the starter generator is powered from
The central DC bus
Can engine start be accomplished with the electrical system in emergency mode
No
The main generators are connected to the electrical system by
Main generator contactors
How many inverters does the aircraft have
2
The number 1 inverter is powered by
DC bus 2
With a total generator failure, the main battery will last for approximately
30 min
The auxiliary generators come on line at
Approximately 70% Np
Is the APU starter generator identical to the main starter generator
Yes
Are the auxiliary generators identical to the main generators
Yes
Can the APU generator be used in flight
Yes
Can the APU generator be used with the battery for engine start
Yes
The primary reason reason for the electrical system to automatically switch from normal mode to emergency mode is
Both main generator fail
During normal flight, auxiliary generators power
DC bus 3 and relay DC bus 3
The backup battery will automatically supply electrical power to the standby horizon when the voltage on EDC 1
Drops below 19 v
Where are the aircraft batteries located
Left nose section
During engine start the main purpose of the backup battery is
To prevent transients affecting certain instruments
In a total electrical failure, the primary purpose of the backup battery is
To power the standby horizon only
The auxiliary generators power the
Auxiliary DC bus
DC bus 3
Relay box DC BUS 3
The backup battery is charged by the
EDC 2
What RPM does the overspeed gov hood Np at
103%
What prevents propeller blades from decreasing below 17.6 at FLT IDLE
Primary low pitch stop
When does the the secondary low pitch stop automatically actuate
When propeller pitch decreases below 12.6
What are the autofeather system requirements
Auto feather switch on
PLA Greater then 62*
Tq above 62*
