AW139 QUESTIONS
AW139 Technical Knowledge Quiz
Test your knowledge on the AW139 helicopter systems with this comprehensive quiz designed for aviation enthusiasts and professionals alike. Each question is crafted to challenge your understanding of fuel systems, flight controls, hydraulics, and more.
Prepare to dive deep into topics such as:
- Fuel Management
- Hydraulic Systems
- Flight Control Mechanisms
- Cockpit Displays
Electronic device that monitors fuel quantity data coming from the fuel probes is
MAU
MRC
EEC
FCU
The purpose of fuel flange in fuel storage system is
For fuel cross feeding when remaining fuel is above 228kg
To transfer fuel between engines when remaining fuel is above 228kg
To balance fuel between tanks when remaining fuel is above 228kg
To purge the fuel line during start when remaining fuel is above 228kg
When the cross-feed valve is open but the pressure in the failed supply line is not restored, it is possible because
Fuel filter clogging
Fuel Leak
Fuel less than 228kg
Fuel supplied in suction mode
A manual feed of the FCU can be operated by selecting the push button FUEL on the TEST control panel when the A/C is
In flight
On ground
Both engine stop
Both generatore online
Where will the copilots PFD obtain air data from after a failure of Air Data Module No. 1?
ADM No. 2 without any pilots action
ADM No. 2 after pilot or copilot action
An alternate static port after proper action
Standby ADM
How can a display unit be turned off?
By setting the corresponding knob on the display DIM control panel to OFF
Using PLT or CPLT knobs on the Reversion Control Panel to OFF
By setting the corresponding switch on the DU PWR control panel to OFF
None of the above
After setting the SOV switch on the hydraulic control panel to 2-CLOSE, what cautions are displayed
2 HYD PUMP, 2 SERVO, 2 HYD OIL PRESS
2 HYD OIL PRESS, 2 SERVO, HYD UTIL PRESS
2 SERVO, 2 HYD OIL PRESS
2 SERVO, HYD UTIL PRESS
Automatic control are provided by the fluid level micro switches located inside the PCM I reservoir if
The fluid in the utility circuit reaches the level 50%, the UTIL SOV will close to stop further drop in fluid pressure
The fluid in the PCM reaches the level of 28%, the TRSOV will close and the UTIL SOV is reopened
The fluid in the PCM reaches the minimum level of 22%, the UTIL SOV of the LDG GEAR EMER circuit will close to stop further drop in fluid pressure
The fluid in the PCM reaches the minimum level 22%, the UTIL SOV will be closed again (TRSOV still closed)
Which system permit testing the flight controls on ground using the electrical pump?
No. 1 hydraulic system
No. 2 hydraulic system
Utility system
None of the above
Where is the cockpit area microphone located?
In the overhead panel
In the instrument panel
In the central console
Not fitted
The serviceability indication on radio altimeter display when pressing Push Test push-button knob at Remote Instrument Controller is:
100 +- 10 ft
100 +- 5 ft
150 +- 10 ft
150 +- 5 ft
What conditions are necessary to fully scroll the CAS message list?
Cursor must be active in the CAS window, all visible caution/advisory messages must be acknowledge, inner knob on CCD must be rotated
Cursor must be active on the MFD, outer knob on the CCD must be rotated
All visible caution/advisory/status messages must be acknowledged, inner knob on CCD must be rotated
All visible caution/advisory/status messages must be acknowledged, outer knob on CCD must be rotated
The display unit are powered by:
Main bus 1 for DU 1 on ground
Essential bus 1 for DU 2 in flight
Main bus 2 for DU 3 on ground
Essential bus 2 for DU 4 in flight
Which statement is incorrect regarding the purpose of the hydraulic power system:
Both systems supply hydraulic power to the flight controls
The no 2 system is used to operate the landing gear in normal conditions
The no 2 system is provided with a Tail Rotor Shut Off Valve
The no 2 system is used to operate the landing gear in emergency situations
The tail rotor shut off valve which is installed on the supply line of the tail rotor actuator,
Of the no 1 hydraulic system
Automatically cuts off the supply of hydraulic fluid in case of the fluids falls below the minimum level
Prevent the fail tail rotor actuator seizure in case of hydraulic pressure drop in the system
Allow the tail rotor actuator to be operated in case of the fluid falls below the minimum level
Which sub-formats are not available to be displayed under MFD system synoptic page?
By setting the corresponding knob on the display DIM control panel to OFF
Engine power synoptic diagram
Hydraulic power system synoptic diagram
AFCS indications
The PFD has a single format and the main function is to provide the following :
Attitude Director Indicator Display
Horizontal Situation Indicator Display
Airspeed indicator
All of the above
Which statement is true regarding DU composite format?
The composite format can only be automatically selected in flight
Automatic reversion to composite format occurs only on flight when the paired DU becomes inactive
Manual reversion can only be selected via the Reversion Control Panel on ground
When the pilot or copilot RCP selectors are returned to NORM, the automatic reversion operations is reset
Crew with visual indications including CAS messages displayed in the CAS window of the Display Units and aural warning messages is provided by:
MAU
MRC
CWS
PMC
The search light is controlled by the five way switch on pilot and copilot collective levers and can extended up to
360
180
110
120
The airspeed trend vector indicator is not displayed when there is no longitudinal acceleration or when the IAS is less than
80 knots
60 knots
40 knots
20 knots
Which is not the FMS combines input of the other aircraft systemsfor output navigation, lateral and vertical commands and aircraft performance predictions?
GPS
ADF
DME
VOR
The vertical fin provides static stability of the aircraft with the following characteristics except:
Minimizing tip vortices created by main rotor at low forward speed
Replaces the tail rotor for anti-torque forces in forward flight
The side force on the vertical fin must be great enough to lift off the tail rotor but, at the same time sufficiently limited to permit autorotation
Prevents dynamic instability
How is the emergency evacuation of the passengers achieved?
By jettisoning the cabin sliding doors
Through the cabin windows
Through the emergency exit doors
Through pilot door
Which statement is true regarding the elastomeric bearing?
Allow a fully articulation of the blades around the flap, pitch and lag axis
Transmit centrifugal forces from the blades to the hub
Transmits the rotation to the swash plate via scissors links
React to lead lag motion and providing blade stops
How is the main rotor speed measured?
Via a linear variable differential transformer
Via a photocell
Via an NR sensor
Via the triple tachometer
Rotor under-speed is accompanied with 3 tones and voice warning ROTOR LOW occur when the rotor speed is below:
95% in AEO power-on flight
95% in power-off flight
95% in AEO power-on flight
95% AEO on ground
How many chip detectors are in the main rotor drives systems?
5
4
3
1
What sensors are located on the intermediate Gearbox?
A pressure sensor, a temperature sensor and a chip detector
A temperature sensor, a chip detector and a bearing thermocouple sensor
A temperature sensor, a chip detector, and an oil low level sensor
A temperature sensor and a chip detector
The ROTOR BRK FAIL caution message is displayed in the CAS window when the following conditions occurs:
The pads are disengaged and there is no pressure in the system
Both engines off, after 10 sec from shutdown of the last engine the caliper is not in down position
One or both engines in ground idle or flight condition after 10 sec the caliper is not in down position
When the system is not pressurized but the rotor brske control lever is in OFF position
Which flight control channels are provided with dual linear actuators?
Pitch, Roll and Yaw
Pitch, Roll and collective
Pitch, Roll, yaw and collective
Pitch and Roll
What action should be carried out after a 2 HYD PUMP caution?
Land as soon as practicable
Land as soon as possible
Continue flight
Land immediately
In case of failure of Hydraulic pump No 2, what caution messages are displayed?
2 HYD PUMP
2 HYD PUMP, 2 SERVO, 2 HYD OIL PRESS, HYD UTIL PRESS
2 HYD PUMP, 2 SERVO, 2 HYD OIL PRESS
2 HYD PUMP, 2 SERVO
1 SERVO or 2 servo caution message indicates:
Relevant system pump has failed
Relevant system has jammed
Relevant system fluid leak
All of the above
The permanent magnetic alternator provides the primary power source for when the engine in running above 40% Ng
FCU
DCU
EEC
FMM
During engine starting, on batteries, how is battery power distributed?
Only the main battery is used to supply the starter generator and all bus bars
The main battery is used to supply the starter generator, while the auxiliary battery is used to feed the essential bus bars
Both batteries are used to supply the starter generator and all bus bars
The aux battery is used to supply the starter generator, while the main battery is used to feed all essential bus bars
At what Ng are the green captions IGN (ignition) and START on the MFD removed during engine start?
IGN at 65% Ng, START at 49% Ng
IGN at 49% Ng, START at 65% Ng
IGN at 49% Ng, START at 49% Ng
IGN at 65% Ng, START at 65% Ng
Which of the following action is necessary for a manual engine start?
Turn on the ENG MODE switch to IDLE
Press the START pushbutton on the ECL with ENG GOV at AUTO
Keep the ENG MODE switch to OFF
Keep the ENG MODE switch at FLIGHT
What is the minimum on-side main bus voltage required prior to starting the engines?
15 volts
18 volts
20 volts
23 volts
The FMM consists of a Fuel Metering Value which control the engine fuel flow in automatic mode or manual mode from the input of :
EEC and Start mofe switches
FCU and ECL
EEC and ECL
FCU and Start mode switches
The Nf over speed protection is active in:
AUTO and MANUAL systems
AUTO mode
MANUAL mode
Flight with AUTO mode
When the ENG GOV selector switches are selected to AUTO, the ECL is able to travel to:
OFF
IDLE
FLIGHT
MAX
PI indicator provides digital readout and analogue indicator in perfect of:
TQ equivalent when the load share switch is selected to TQ
Ng equivalent when the load share switch is selected to Ng
Nf equivalent when the load share switch is selected to Nf
ITT equivalent when the load share switch is selected to TEMP
The time limit for operating AEO at take-off power limit and OEI at maximum continuous power limit is:
30 sec
1 min
2.5 min
5 min
Where are the cockpit ventilation Ram Air inlets located?
In forward sliding fairing
In both cockpit doors
Underneath the forward fuselage
Above the cockpit AUTOFLIGHT
Which of the following procedures must be performed by the pilot before each flight in order to use the FMS?
FMS preflight test, position initialization and flight-plan activation
Position initialization, Flight-plan activation and performance initialization
FMS and GPS preflight test, position initialization, Flight-plan activation and performance initialization
Position initialization and performance initialization
What happens when the PUSH SYNC button on the HEADING knob is pressed?
The heading bug aligns with the current aircraft aircraft course
The heading bug aligns with the current aircraft heading
The heading bug aligns with the current bearing pointer No. 1
Engage the heading mode with the current aircraft heading
During the preflight procedure, as part of the system check, pilot is required to perform a AFCS TEST that is initiated by pressing the TEST button on the Autopilot controller with the following condition:
WOW on
Electrical and hydraulic power available
Autopilots disengaged
All of the above
The default rate of descent when engaging the ALTA is:
500 feet/min
750 feet/min
1000 feet/min
1250 feet/min
How can the GA mode engaged?
Pressing the GA pushbutton on the guidance controller or on the collective provided that the helicopter height is not less than 150 feet AGL
Having set DH and pressing the GA pushbutton on the collective or on the guidance controller
Pressing the GA pushbutton on the collective provided that the airspeed is higher than 60 KIAS
The FMS will engage the GA mode automatically in approach mode
In case an unflagged miscompare occurs between the two AHRS which input is used by the MAU to determine which AHRS has failed?
Standby instrument
Flux detector
ADS
ADI
Which of the following actions permit recovery after 1-2 AHRS fail caution message?
Move AHRS selector on RCP to 1, select DG mode on both AHRS and use magnetic Compass for magnetic heading
Move AHRS selector on RCP to BOTH, re-engage AP2 and use STBY Instrument for attitude and magnetic heading
Use STBY Instrument for attitude and magnetic compass for magnetic heading
Move AHRS selector on RCP to 2, select DG mode on both AHRS and use magnetic compass for magnetic heading
Pressing the SAS REL button on the cyclic grip:
Disengage the FD
Disengage the trim actuator momentarily
Disengage the force trim release
Disengage the AP
The minimum speed for IAS mode engagement is
80 knots
60 knots
40 knots
20 knots
When the RAD MSTR switch is set to GND which MRC modules available?
NAV 1
VHF 1
ADF
DME
How is the Push-To-Transmit keying achieved?
Using the foot switch
Using the foot switch or in backup mode by using the cyclic switch
Using the cyclic switch or the foot switch
Using the cyclic switch
One engine is running, external power is connected to the helicopter and EXT PWR switch is ON, what supplies power to the starter when starting the second engine?
External power
External power and main battery
Generator and main battery
Generator
Bus tie will remain open when:
Short circuit
Bus tie on
One of the generators online
External power is connected and switch on
Which Bus Bars are not powered if generators no. 2 fails?
MAIN 2
ESS 2
NON ESS 1 and 2
MAIN 1
Where is the landing gear control panel located?
Pilot side only
Copilot side only
Both pilot and copilot sides
Central console
The purpose of two fuel feeding lines are connected to each other by the cross feed valve is to permit and allow:
In case of any drop of pressure, one of the tank feeds the other tank
In case of any drop of pressure, one of the tank feeds the other engine
In case of any drop of fuel quantity, one of the tank feeds the other engine
In case of any drop of fuel quantity, one of the tank feeds the other tank
Two Low Level Sensors are installed on the lower part of the secondary probe provide the caution 1 (2) FUEL LOW when the fuel level quantity drops below
82 kg
92 kg
112 kg
228 kg
Which statement is not true regarding the fuel cross-feed valve when the fuel cross-feed switch is set to normal?
Automatically closed in normal operation
Automatically opened as result of single fuel line pressure drop
Automatically opened as a result of booster pump failure
Automatically closed in the event of engine on fire.
How is fuel availability affected by automatic cross-feeding (XFEED switch to NORM)
Part of fuel content in one tank cannot be supplied with the operating pump
Fuel content can be supplied until the FUEL LOW caution is illuminated.
All the fuel content in the tanks can be supplied
All the fuel content in failed tank can be supplied
The hydraulic electrical pump is equipped with a 2 minutes timer relay used to
Save battery power
Prevent the pump from overheating
Prevent the hydraulic from overheating
All of the above
They hydraulic Flight Controls circuit shut-off valves allow the isolation of the flight controls from hydraulic circuit in case of:
Hydraulic filter clogging
Flight control servo jammed
System under pressurized
System overheating
How does the 50% level switch in PCM 1 affect the system operation?
The Utility SOV 1 is closed and the 3 amber lights on the LDG GEAR control panel illuminate
The Utility SOV 1 closed and the 1 HYD MIN caution is displayed in the CAS.
There is no effect on the system operation and no caution message is displayed in the CAS.
1 HYD MIN caution is displayed in the CAS
What would be the pressure indication in the Hydraulic System No.1, with the SOV switch on the HYD Control Panel set to 1-CLOSE?
0 bar
About 207 bar
About 65 bar
About 112 bar
The correct arrangement for the 4 Display Unit are:
DU 1 Co-pilot PFD
DU 2 Pilot PFD
DU 3 Co-pilot MFD
DU 4 Pilot MFD
What is the meaning of the DG1 amber indication on pilot PFD?
AHRS selector on the RCP is set to 1.
Pilot has selected DG mode and co-pilot has taken control on AHRS 1.
AHRS 1 Directional Gyro has failed so there is no backup available for pilot HIS.
AHRS selector on the RCP is set to 2.
What other visual indications are there when a red CAS message is displayed?
The Master Caution Light flash
The Master Warning Light flash
The Master Warning and Master Caution Lights flash
Associated system Master Warning Light flash
What is the MFD display format that is set to default at power up?
Power plant
System
Plan
Map
Which of the following aural messages is continuously repeated until the condition is corrected?
ROTOR HIGH
ROTOR LOW
ENGINE OUT
BAG FIRE
Which of the following statement regarding the Emergency Locator Transmitter System is correct?
The ELT automatically transmits both tone and encoded data on the VHF Guard frequency
The ELT Switch can be used to stop an automatically-activated transmission
The ELT Batteries are automatically recharged during flight.
The ELT is powered by aircraft standby battery.
Which Aural Warning Message is inhibited by setting the AWG Switch to INHIBIT?
Airspeed
Aural System Test
150 feet
Check height
Composite format is reduced PFD format with the addition of the following except:
Crew Alerting System messages
Pressure readouts for Engines, Main Gearbox and Hydraulic Power systems
Temperature readouts for Engines and Main Gearbox
Fuel Quantity indicator
Which control panel is used to manage data and control all the DU designator and radio tuning?
RIC
CCD
DC
RCP
When a warning occurs, the MWLs start to flash until any pilot resets by either pressing MWL or CAS RST push button which located at:
Collective
Cyclic
Central Console
Overhead Console
The MPFDR unit (or FDR/CVR) is a solid state airborne recorder and consists of a solid state memory module and is able to store a minimum of hours of aircraft data.
120
12
52
25
The Glide Slope scale for the ILS consists of a rectangle with two dots above and below it where each dot represents a graduation of above or below glideslope on an ILS approach
0.5°
1.0°
1.5°
2.0°
The DIM control panel allows individual brightness adjustment of the
Central console
Instrument panel
Display units
Overhead panel
The navigation system is integrated in the avionic system includes the Air Data System which providing the information except:
Airspeed
Attitude
Vertical speed
Outside air temperature
The decision height can only be set when the radio altitude is below:
4500 feet
3500 feet
2500 feet
1500 feet
The primary controller for the FMS is the:
PFD
MFD
CCD
MCDU
The strake is an aluminium device mounted on the upper left side of the tail section which produces an aerodynamic force that improves the helicopter performance in:
Forward flight
Autorotation
Hover
Descending
How many jettisonable window emergency exit from the inside to the outside of the AW139 helicopter?
4
6
8
10
A rotor speed probe is used provides three independent analogue outputs signal of the main rotor speed used by the:
FCU
NIM
EEC
NIC
Rotor over-speed is accompanied with 2 tones and voice warning ROTOR HIGH occur when the rotor speed is above:
110 % in AEO power on flight
110 % in power-off flight
110 % in OEI power-on flight
110 % AEO on ground
Which of the following is not the accessories driven by the MGB?
MGB oil cooler fan
Hydraulic power pumps
ECS compressor
MGB emergency lubrication pump
What is the recovering action, if after third activation of the chip burner, the MGB CHIP SUMP caution remains?
Reduce power and land as soon as practicable
Land immediately
Reduce power and continue flight
Land as soon as possible
The CLPR up green LED on the Rotor Brake Pressure Indicator is lighted when:
On ground all engines on and WOW off
In flight all engines ON and WOW off
On ground all engines off and WOW on
In flight all engines ON and WOW on
The purpose of Linear Variable Differential Transformer installed at the left end of the Collective torsion lube is for:
Sensing the collective position for engine power anticipation
Sensing the collective position FD altitude anticipation
Sensing the collective position for Auto-pilot altitude change anticipation
Sensing the collective position for turn coordination anticipation
What is the main function of the Hydraulic Electric Pump?
To provide hydraulic power to the flight controls for the full and free movement check
To provide hydraulic power to the Landing Gear in case of No 1 System failure
To provide hydraulic power to the servo actuators in case of failure of hydraulic pump no 1 during flight
To provide hydraulic power to the servo actuators in case of failure of Hydraulic Pump No 2 during flight
How can the SOV switch on the HYD Control Panel be used to recover after a “HYD UTIL PRESS” caution?
SOV switch moved to 1-CLOSE
SOV switch moved to 2-CLOSE
SOV switch is ineffective to recover
SOV switch moved to 1-CLOSE then select the SOV switch to normal
In case of failure Hydraulic Pump No 1, what caution message displayed?
1 HYD PUMP
1 HYD PUMP, 1 SERVO, EMERG LDG PRESS
1 HYD PUMP, 1 SERVO, 1 HYD OIL PRESS, EMERG LDG PRESS
1 HYD PUMP, 1 SERVO, 1 HYD OIL PRESS
Which other caution messages could be triggered at the same time as the 1 SERVO caution?
EMER LDG PRESS in case of loss of pressure in the system
HYD UTIL PRESS if the SOV switch on the HYD Control Panel is set to 1-CLOSE
1 HYD MIN
4 HYD PUMP
In addition to a SAS Mode selection, when will the AP automatically disengage the ATT mode?
Yaw/Collective trim is disengaged
Collective Trim is disengaged
Cyclic Trim is disengaged
Yaw trim disengage
The AW139 is powered by 2 free turbine turbo shaft propulsion engine that includes______ stage axial compressors, ______ stage centrifugal compressor and the compressors are driven by a _______ stage compressor turbine.
2,1,2
4,1,2
1,4,1
4,1,1
What is the first action in case of an ENG CHIP caution?
Select the ECL to OFF
Achieve a safe OEI flight and move the ENG MODE to IDLE.
Activate the chip burner
Select the Start Mode Switch to OFF
On which collective Control Grip are the ENG GOV Switches located?
Pilot and co-pilot
Pilot only
Co-pilot only
Not fitted on the collective
When flying with the ENG GOV at MANUAL, what is the required position of the ENG MODE switch?
The ENG MODE switch position is not relevant
The ENG MODE switch must stay in the IDLE position
The ENG MODE switch must stay in the OFF position
The ENG MODE switch must stay in the FLIGHT position
How will the engine respond when setting the Engine Control Lever to OFF with the ENG MODE switch at FLIGHT?
The engine flames out
There is no change in engine response
Engine responds slowly
Engine stabilize at idle
What is the maximum time allowed for the engine light up?
5 seconds
10 seconds
15 seconds
20 seconds
The Nf limiter is an independent subsystem that activate the over speed protection when the Nf value reach:
107% NF
109% NF
111% NF
112% NF
Which parameter can be selected with the LD SHARE switch to match the engine?
Nf
Ng
PI
ITT
In DU composite format, the engine oil pressures is indicated by:
Digital and analogue readout
Digital readout only
Analogue readout only
None of the above
In what range, can the Engine Control Lever (ECL) be moved using the ENG TRIM selector on the collective grip?
From MIN to MAX in AUTO
From FLIGHT to MIN in MANUAL
From MIN to MAX in MANUAL
From FLIGHT to MAX in MANUAL
The environmental control system consists of the following sub-systems except:
Ventilation
Defogging
Heating
Air conditioning
Which is the axis not provided with limited control input by the Dual Linear Actuators?
Pitch
Roll
Yaw
Collective
When FMS 1 or 2 is selected as the Primary Navaid, what is the effect of the rotation of the COURSE knob on Remote Instrument Controller?
No effect
VOR Course value is modified
Desired track value is modified
LOC course value is modified
What will also happen if the AHRS 2 fails?
FMS 2 is automatically disengaged
AP 1 is automatically disengaged
AP 2 is automatically disengaged
FMS 1 is automatically disengaged
The AP Trim Master is determined by:
AP 1
AP 2
First AP selected on
Switching on the trim master switch
What happens if the cyclic FTR switch is pressed while the Flight Director is in HDG mode?
The AP roll channel starts following the HDG mode
The AP roll channel ignores the HDG mode
The AP roll channel continues to follow the HDG mode
The aircraft will resume last heading before FTR engagement
What amber message is provided in reverse video on the PFD when roll data differs from the different sources?
ROLL
ATT
SAS
AHRS
The cyclic position indicator is displayed on the ADI to help pilot center the cyclic controls and the indicator is only displayed when the helicopter is:
On the ground
In Flight
WOW on and Collective at MPOG
WOW off and Collective at MPOG
The default Rate of Climb when engaging the ALTA is:
500 feet/minute
750 feet/minute
1000 feet/minute
1250 feet/minute
If the APP mode is continued to below landing minimum, the auto level safety of feature is automatically activated and the aircraft will level of at:
150 feet radio altimeter
150 feet barometric altimeter
50 feet barometric altimeter
50 feet radio altimeter
What the type of audio signals interface The VHF1 radio transceiver and the co-pilot audio control panel?
Digital audio buses
Analogue stereo standard wiring
Both digital audio buses and analogue standard wiring
Stereo buses only
Which is not the Generator Control Units function?
Overvoltage
Under voltage
Overcurrent
Undercurrent
With both engines at 100% Nf and External Power ON, when will the Generators be supplying power?
As soon as the GEN switches are set to ON
As soon as the EXT PWR switch is set to OFF
As soon as the generator output is 0.5 Vdc higher than the External Power voltage
As soon as WOW off
Which of the following conditions will allow the Main Bus No 2 to be energized with the helicopter on the ground and both batteries available?
BATTERY MASTER Switch ON, BATTERY MAIN switch ON, BUS TIE switch ON
BATTERY MASTER Switch ON, BATTERY AUX Switch ON, BUS TIE Switch Auto
BATTERY MAIN Switch ON, BUS TIE Switch ON
BATTERY MAIN Switch ON, BUS TIE Switch AUTO
What indication is shown on the NOSE WHEEL CENTERLOCK pushbutton if the button is pressed to lock, but the locking pin is not engaged in the flange hole?
No lights are illuminated on the pushbutton
The UNLK amber light is flashing on the pushbutton
Both the UNLK amber light and the LOCK green light illuminated on the pushbutton
The LOCK green light are illuminated on the pushbutton
What is the correct sequence of actions when setting the parking brake?
Pull and rotate the parking brake handle clockwise and push the brake pedals until the “PARK BRK ON” advisory appears
Pull and rotate the parking brake handle clockwise and push the brake pedals until the “PARK BRK PRESS” caution appears
Pull and rotate the parking brake handle anticlockwise and push the brake pedals until the “PARK BRK ON” advisory appears
Pull and rotate the parking brake handle anticlockwise and push the brake pedals until the ‘PARK BRK PRESS” caution appears
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