|Prior to first engine start, electrical system indications are displayed where? PFD 1 MFD 1 MFD 2 MFD 1 and MFD 2.
When connected and powered, the EPU charges the aircraft battery? Yes, if the battery switch is in the BATTERY position. Yes, if the battery switch is in the BATTERY or EMER position No, the EPU connects to the Hot Bettery Bus which is prior to the Battery relay. Yes, the EPU connects to the Hot Battery Bus which is prior to the Batter relay.
Battery power supplies ____ minutes if the battery switch is in EMER position, with a loss of all engine driven power sources in flight. 25 minutes. 60 minutes. 30 minutes. 88 minutes.
With the BATT DISC Switch in the DISC position, the battery disconnect relay is powered by: Battery with BATTERY Switch in ON (available power for 12 hours) Standby attitude indicator battery (available power for 88 minutes) Relay is not powered, it is mechanical Generator power since the battery is disconenected.
The light in the ENGINE STARTER buttons illuminate to indicate: Starting is complete Opening of the start relay Closing of the start relay Generator disconnect.
The máximum generator amps on the ground is: 300 240 170 200.
What is the difference between an amber and a red GENERATOR OFF L-R message?
One generator off line indicates amber, both generators off line indicates red. Both generator off line indicates ambers, both generators off line and both alternators off line indicates red. If one generator relay is tripped the message indicates amber, if one generator field is tripped the message indicates red. One generator off line for more than 20 seconds and low voltage on the battery, the message indicates a red, one generator off line for less 20 seconds, the message indicates amber.
What does a red AD-DC CONVERTER FAIL message indicate? Both alternators are opening normally Both geneators are operating normally This red message does not exist Both generators have failed and the aircraft is on battery power only.
What do the engine-driven aternator (AC) normally power? Collins flight displays Collins flight displays and Collins FMS CDU Collins flight displays, FMS CDU, and heated windshield Only the heated windshield.
What are the memory ítems with a red BATTERY FAIL message: Note volts and amps, BATTERY Switch – OFF, Notes volts and amps. Note volts and amps, BATTERY Switch – EMER, note volts and amps. Shut off Generator and BATTERY Switch to EMER, alternators provide power to the
Note volts and amps, alternators to OFF, Note volts and amps.
What is the function of the transformer rectifier unit (TRU) ? Converts DC to AC power in order to power the AC converted power buses. Converts AC to DC to normally power the DC powered heated windshield, or the converted power bus in an emergency. Converts AC power to DC power in order to power the DC converted power buses. Monitors the AC alternators and maintains proper paralleling between the left and right alternator.
When would an alternator power the battery bus? Alternators can never power the battery bus, only the heated windshield. Alternators power the battery bus with a dual generator failure and the heated windshield switch in the OFF position. Dual generator failure, the right alternator power the TRU which powers the hot battery bus. Dual generator failure, the left alternator powers the TRU and the right alternator powers half the heated windshield.
What condition makes the left alternator power the battery bus? Dual generator failure and a right alternator failure. Dual generator failure, the left alternator powers the TRU and the right alternator and the right alternator powers half the heated windshield. Dual generator failure and battery power is below 24 volts. Dual generator failure and only the PFD 1 and MFD 1 are available.
With the generators online and no external power, the battery is isolated from any charging source when the BATTERY switch is in:
ON OFF EMER Both OFF and EMER.
What is the máximum cruise altitude with a dual generator failure (alternators working) ? FL240 FL350 FL410 FL450 .
What is the function of the DAY position on the instrument lighting panel?
Turns the instrument panel to high intensity Turns the instrument panel off Turns the instrument panel to high intensity and brightnes electronic charts Turns the instrument panel off and brightnes electronic chart.
What initially turns on the cabin overhead lights? The Battery Switch to ON turns on the cabin overhead lights. The entry light switch automatically turns on the cabin overhedad light. The 1st push of the cabin lights on the client switch panel. The 1st push of the cabin lights before the battery switch is selected on.
Amber EMER LIGHTS NOT ARMED message is the result of The EMER LIGHTS switch in the ARMED position and the emergency ligts tail to illuminate. The EMER LIGHTS switch in the ARMED position and the emergency lights fail to illuminate The EMER LIGHTS switch in the OFF position The aircraft experiencies 2 Gs of lateral force but the emergency lights do not .
The INT MASTER switchlight in the OFF position will: Remove all electrical power to the lights in the cabin except emergency lights. Remove all electrical power to the lights in the entire aircraft. Turns on all lighting in the cabin of the aircraft. Removes all electrical power to lights in the cockpit.
How can the pilot determine if the beacon light is activated? White indicator light on the BEACON switch is not illuminate. Amber indicator light on the BEACON switch is illuminated. Cyan indicator light on the BEACON switch is illuminated. CAS message and White halo around BEACON switch is not illuminated.
The TCAS switchlight can be armed on the ground with LNDG lights ON: True – if the transponder is selected to ON and ALT. False – only one mode can be selected at a time. True – landing light will automatically switch to TCAS at 500 feet. False – Squat switch logic prevents ground pulse lights.
Where are CAS messages displayed during the 1 st engine start (avionics switch in DISPATCH) ? PFD 1 PFD 2 MFD 1 MFD 2.
Where are CAS messages displayed during normal flight operations? PFD 1 PFD 2 MFD 1 MFD 2.
If a new red CAS message appears It is displayed at the top of the red group of the CAS messages. The message and the MASTER WARNING switch light will flash until depressed. The voice annunciation will repeat the message until the MASTER WARNING button is pushed. All answers are correct.
Amber CAS messages: Are grouped below red CAS messages. Will cause an aural message stating the CAS message. Will cause the MASTER CAUTION switch light to steadily illuminate. Are grouped below red CAS messages and will cause the MASTER CAUTION switch light to steadily illuminate.
Cyan CAS messages: Require immediate checklist procedures. Require a memory ítem action. Are normal considered advisory only. Have no emergency procedures.
Aural alerts will always: Alert what CAS message appears at the time. Alert the highest priority CAS message. Alert every CAS message in sequence. Alert all CAS messages. .
System test is accomplished by: LWR menú on PFD 1, controlled by the DCP. UPR menú on PFD 1, controlled by the DCP. LWR menú on MFD 1, controlled by the CCP. UPR menú on MFD 1, controlled by the CCP.
What is the total capacity of the fuel system? 6.000 lbs 5.828 lbs 5.180 lbs 5.018 lbs.
The SPR system: Is a service pressure regulator for venting back pressure in the fuel. Is a single point refuel/defuel system. Is supplemental priest recycling for reusin fuel additives. Is a FDU mode for adding fuel during start sequence.
If an amber FUEL LEVEL LOW message appears: The respective wing quantity has just reached 200 pounds. The boost pump on that side will automatically actívate. The pilot must manually turn on the boost pump. The MASTER WARNING light illuminates.
What is the function of the surge tank? Allows extra fuel to be used during extended flights. Acts as an overflow tank and is fed by the climb vent vane. Stores fuel bypassed by the FDU for ejection pump use. Contains the electric fuel pump and is the main pickup for the engine.
What is the function of the scavenge ejector pumps? Pressurize fuel for the slinger ring. Move fuel from other áreas in the wing tank for transfer to the other wing. Move fuel from other áreas in the wing tank for transfer to the other engine. Moves fuel from other áreas in the wing tank to that tanks Hopper.
Fuel transfer knob allows fuel to be transferred:
From wing to wing. From wing to engine. From engine to SPR. From SPR to wing.
What is the difference between the amber and cyan FUEL TRANSFER CAS message? Cyan indicates transfer valve open and imbalance greater than 60 lbs, Amber indicates transfer failure. Cyan indicates transfer failure, Amber indicates the fuel transfer valve is open and an imbalance greater than 60 lbs in the direction of transfer. Cyan indicates normal transfer, Amber indicates the fuel transfer valve is open and an imbalance greater than 60 lbs in the direction of transfer. Cyan indicates normal transfer, Amber indicates transfer failure.
When using SPR, how is the fuel delivery stopped when the wing (s) are full to prevent overfueling? The pilot valve will open by rising with the fuel and allow incoming fuel to close the SPR refuel valve which will stop incoming fuel flow. The pilot valve closes and prevents fuel from entering the SPR refuel valve. The pilot valve open when the wing is pressurized which will allow some fuel to enter the vent tank. The pilot valve electrically activates the dead man switch and shut off fuel flow from the truck, requires electrical power (28 VDC).
What position must the precheck levers be in for defuel operations? Closed Open Defuel Normal.
If fuel transfer has been selected and normal and converted DC electrical power is lost: The system continues to transfer fuel. The transfer valve fails close, and the boost pump stops working. The boost pump is energized by the alternators to continue transfer. Continue normal flight to destination.
Asymetric fuel limitations are: 400 normal; 800 emergency 200 normal; 800 emergency 200 normal; 600 emergency 400 normal; 1000 emergency
What is the result if the pilot depressed the IGNITION – MANUAL button? Commands one ignitor. Commands both ignitors. Commands both ignitors on the ground only, no manual function in flight. Commands one ignitor only in flight.
The OIL FILTER BYPASS message indicates: Aircraft is grounded and maintenance is required. Aircraft may be flown for up to 5 hours of flight after the CAS message appears. Informative message resets with a normal DC power cycle. Message may be cancel after pressing FADEC reset buttons.
The limitation for the engine oil for the CJ4 are: Only use Mobil JET II or Mobil 254. Approved oils may be mixed. Oil must be checked during pre and post flight inspections. All other answers.
Where are the oil temp and oil pressure indications normally displayed in flight? PFD 1 PFD 2 MFD 1 MFD 2.
What normally powers FADEC in flight? Hot battery bus. Crossfeed bus. Coverted bus. PMAs in the FDU.
A red ENGINE FAILED L – R message indicates:
N2 is below idle. RUN/STOP switch is in RUN. Engine is not in a start sequence. All other answers.
Pressing the ENGINE STARTER switchlight: Commands only engine starter. Commands the engine starter and ignition. Commands the engine starter, ignition and add fuel flow. Commands the engine starter, ignition, fuel flow and PMA.
What activates ignition during a normal engine start? RUN/STOP switch Pilot controlled IGNITION-MANUAL switch ENGINE STARTER switchlight Moving the throttle from OFF to IDLE position.
If the fire bottle was used, activated by the pilot, what CAS message would advise the pilot of that action? Cyan ENG FIRE BOTTLE LOW. Amber ENG FIRE BOTTLE LOW. No CAS messaged, the onside BOTTLE ARMED switchlight extinguishes, the other BOTTLE ARMED switchlight remains illuminated. No messages are indicated-pilot action.
A Flashing green light on the bottom of the forward baggage smoke detector indicates: Battery in the smoke detector is bad (low voltaje) and needs to be replaced with a 9 VDC battery from Cessna. Detector is operational, normal. Detector is nor receiving a charge and requires the SMOKE DETECTOR switch to be place in EMER. Detector is sensing a yellow refraction in reflectivity with the pulsating blue LED.
A red ENG FIRE L – R message indicates: Excessively high temperature is sensed in the engine burner can. Excessively high temperature is sensed in the engine exhaust. Excessively high temperature is sensed in the engine cowling. Excessively high temperatura is sensed in the engine intake.
What message displays if a fire occurs in the nose baggage compartment? Amber BAGGAGE SMOKE FWD.
Red BAGGAGE SMOKE.
Red BAGGAGE SMOKE FWD. Amber BAGGAGE SMOKE.
What CAS displays if a fire bottle is armed (ENG FIRE switchlight is pushed)? Cyan FUEL F/W SHUTOFF message appears. Cyan HYD F/W SHUTOFF message appears. Amber DC GENERATOR message appears. All other answers.
What would result if the pressure in the Fire-Extinguishing Bottle in the tailcone increases too high due to temperature? The bottle burst and the cyan ENG FIRE BOTTLE LOW message appears. The bottle discharges into the engine and the red ENGINE FIRE L – R message appears. The temperature compensated pressure switch (TCPS) discharges the bottle and the cyan ENG FIRE BOTTLE LOW message appears. The temperature compensated pressure switch (TCPS) discharges the bottle and the amber ENG FIRE BOTTLE LOW message appears.
What air ducts inside the aircraft are supplied if the AIR SOURCE SELECT switch is in the L position? Cockpit Cabin Cockpit and Cabin None.
What air ducts inside the aircraft are supplied if the AIR SOURCE SELECT switch is in the R position? Cockpit Cabin Cockpit and Cabin None.
What happens when the AIR SOURCE SELECT knob is selected to FRESH AIR? Draws air to the cabin from the right pylon and turns on a blower. Closes both PRSOVs, stopping air from the engines to reach the cabin. Maintains normal service air. All other answers.
The TAILCONE BLEED LEAK detection is tested during the BLEED LEAK system test. True False.
What happens if the aircraft system detected a pylon leak? The PYLON BLEED LEAK message appears. Both the ECS and wing anti-ice PRSOVs on that side close automatically only if the SOURCE knob is in NORM. Both the ECS and wing anti-ice PRSOV son that side close automatically regardless of the position of the SOURCE knob. The PYLON BLEED LEAK message appears and Both the ECS and wing anti-ice PRSOVs on that side close automatically only if the SOURCE knob is in NORM.
What is the difference between a cyan and an amber PRESSURE SOURCE NOT NORM message? Cyan indicates SOURCE knob is not in NORM in flight. Amber indicates SOURCE knob is not in NORM on the ground. Amber indicates SOURCE is not in NORM in flight. Cyan indicates SOURCE knob is not in NORM in flight and Amber indicates SOURCE knob is not in NORM on the ground.
What results if the aircraft is in flight with both wing anti-ice on and the amber WING BLEED LEAK L message appears? The wing anti-ice valve remains open and flight may be continued as normal. The wing anti-ice valve closes stopping bleed air to the wing, pilot must start checklist procedures. The wing anti-ice valve closes and CAS message disappears, pilot has no checklist procedures. The wing anti-ice valve remains open but the pilot must start checklist procedures.
What happens if a leak is detected and the SOURCE knob is not in the NORM position? There is not any indication or automatic PRSOV activation Both wing anti-ice valve close, stopping bleed air to the wing. Pilot initiates checklist procedures There is an appropriate CAS message but the corresponding PRSOV remains open. There is not any indication but the corresponding PRSOV automatically closes.
What is the temperature indicated in visible moisture in which icing conditions exist in flight? RAT 10 C SAT 10 C RAT 5 C SAT 5 C.
What ítems are heated with the PITOT/STATIC HEAT 2 switch? Pilot`s pitot tubes, static ports and the standby pitot tube. Copilot`s pitot tubes, static ports, and AOA vane. Pilot`s and copilot`s pitot tubes and static ports. Only the standby pitot tube and the AOA vane.
What does an amber PITOT/STATIC COLD L-R-STBY message indicate? The appropriate PITOT/STATIC HEAT switch is selected on but the appropriate ítems are not receiving heat. The appropriate PITOT/STATIC HEAT switch is selected off and the appropriate ítems are not receiving heat. The appropriate PITOT/STATIC HEAT switch is selected off and the throttles are greater than a TLA of 11.5º on the ground only. The appropriate PITOT/STATIC HEAT switch is selected on but the appropriate ítems are not receiving heat and the appropriate PITOT/STATIC HEAT switch is selected off and the throttles are greater than a TLA of 11.5º on the ground only.
What is the tail boot inflation and deflation cycle? Left inflates for 6 seconds immediately followed by the right for 6 seconds, cycle repeats every 2 minutes. Left inflates for 6 seconds then no boots for 6 seconds the the right boot for 6 seconds, cycle repeats every 3 minutes. Both boots inflate at the same time for 12 seconds, cycle repeats every 2 minutes. Both boots inflate at the same time and remains inflated as long as the pilot presses and holds the TAIL DEICE switchlight.
What does the amber TAIL DE-ICE FAIL L-R message indicate? Boot inflation cycle is wrong – time failure. The tail de-ice system has failed. Both boot inflation pressure is below 16 psi. All other answers.
Regarding windshield heat It`s operating anytime the engine are running It requires DC power from the generators The W/S HEAT switchlight on the ICE PROTECTION panel is used to actívate the system It should be used anytime RAT is +10 C or colder.
What does the PILOT FAN or COPILOT FAN knobs control? Both knobs adjust the volume of airflow through the vortex cooler. Both knobs adjust the volume of airflow through the fresh air blower. Each knob independently controls the appropriate evaporator fan speed. Each knob independently controls the appropriate fresh air fans.
When does the air condition compressor operate? If the CLIMATE CONTROL knob is in NORM, the ECS commands the compressor on or off as required. If the CLIMATE CONTROL knob is in COMP ON, the compressor is commanded on all the time. Below 28.000 feet. All other answers.
How would a generator failure in flight affect the air conditioning compressor? The compressor automatically shuts off for electrical load shedding. The compressor continues to operate but at a reduced output. The compressor continues to operate but as normal. The compressor automatically shuts off but can be restored with checklist procedures.
The COCKPIT DUCT OVERTEMP message indicates: Supply line to the cockpit has exceeded normal operation temperature. Supply line to the cockpit has exceeded normal operation pressure. Common supply line to the cockpit and the cabin has exceded normal operation temperature. Supply line to the cabin has exceeded normal operation temperature.
What switch position(s) are required to allow the cabin management system (CMS) to control the cabin temperature? CABIN TEMP – PASS CABIN TEMP – REMOTE COCKPIT TEMP – REMOTE COCKPIT TEMP and CABIN TEMP – PASS.
Where does the pressurization controller get the landing field elevation information? FMS entries. Manual settings on PFD 1 displayed on MFD 1. Manual setting on MFD 2. FMS entries and Manual settings on PFD 1 displayed on MFD 1.
How does the pilot know when the pressurization controller is in HIGH ELEVATION mode? Cyan HIGH ELEVATION message. Amber HIGH ELEVATION message. Red CABIN ALTITUDE message. Cyan HIGH ELEVATION message and Amber HIGH ELEVATION message.
Where is the CAB RATE of climb displayed? On the FMS CDU1. On the PFD 1 lower format. On the MFD 1 lower line. On the MFD 2 CAS message section.
What occurs if the pilot pushes the CABIN PRESSURE-DUMP button? The outflow valves closes, and the cabin depressurizes. The outflow valves open, and the cabin depressurizes. The PRSOV closes, and the cabin depressurizes. The PRSOV opens, and the cabin depressurizes.
What is the cabin altitude if the red CABIN ALTITUDE message displays? Approximately 10.000 feet in all modes. Approximately 10.000 feet in normal mode. Approximately 15.000 feet in high elevation mode. Approximately 10.000 feet in normal mode and 15.000 feet in high elevation mode.
The only hydarulic fluid approved for the CJ4 is: MIL – PRF -83282 MIL – PRF – 5606 SKYDROL MIL – PRF – 87257.
The hydraulic fluid level can be checked: At the hydraulic service panel, must have BATTERY switch ON. At the hydraulic service panel, BATTERY switch may be ON or OFF. Hydraulic reservoir dipstick, reservoir must be depressurized. Service mule gauge only.
The pilot may display hydraulic pressure levels in normal flight on: Hydraulic service panel. MFD 1 or 2. PFD 1 or 2. FMS CDU.
The cyan HYD F/W SHUTOFF L message indicates:
Left hydraulic pump has internally failed. Left hydraulic pump is over pressure. Pilot pressed the HYDRAULIC SHUT-OFF switchlight on the left side. Left hydraulic pump is over pressure or Pilot pressed the HYDRAULIC SHUT-OFF switchlight on the left side.
The subsystems of the hydraulic system are: Landing gear and brakes, flaps and speedbrakes. Landing gear, flaps and speedbrakes only. Landing gear, flaps, speedbrakes and ground spoilers. Speedbrakes and ground spoilers and brakes.
The red landing gear indicators indicate: Inner gear doors are open. Gear is not down and locked. Gear is in transit. Gear position differs from the handle position.
The landing gear aural warning sounds if the throttles are below CRU detent and: Gear is up and flaps are >15º. Gear is up and aircraft is below 500 feet AGL and throttles <CRU. AOA is >0.4 and radar altimeter has failed. All other answers.
Emergency extensions of the landing gear requires: Use the checklist and pull the AUXILIARY GEAR CONTROL only. Use the checklist and pull the AUXILIARY GEAR CONTROL then pull the red EMERGENCY GEAR BLOWDOWN to activate the nitrogen bottle. Use the checklist and pull the AUXILIARY GEAR CONTROL then side load the aircraft for main gear extensión. Use the checklist and PUMP the AUXILIARY GEAR CONTROL until 3 green and no red indication.
What does the amber WT ON WHEELS MIS-COMPARE message indicate? Weight on one of the main wheels differs 12.8 pound from the other. Squat switch signals disagree for greater than approximately 12.8 seconds. Squat switch signals disagree at any time. FMS weight and the squat switch signal weight differs 12.8 pounds.
If heavy braking was required, and the brakes are excessively high in temperature: The tires increase in pressure and ruptures. The tires deflate through the fuseplugs. The tires start to adhere to the taxi Surface. The TIRE OVERTEMPERATURE-WOW THAT WAS CLOSE message indicates.
When is antiskid protection not available? During initial touch down-prior to wheel spinup. If ANTISKID FAIL CAS is posted. Taxi speeds below 12 kts for taxiing maneuvers. All other answers.
The ANTI SKID FAIL message displays: Only if the antiskid circuit breaker is pulled. If the antiskid circuit breaker is pulled or during the antiskid test. If the selection of BRAKE TEST on system test. Only if the system requires maintenance.
During emergency braking: The antiskid system modulates brake application with normal DC. The EMER BRAKE handle routes hydraulic pressure to the Wheel brakes, bypassing the antiskid servo valve. The EMER BRAKE handle routes hydraulic pressure directly drom the engine driven hydraulic pumps to the Wheel brakes. The EMER BRAKE handle routes nitrogen pressure directly to the Wheel brakes.
The CTRL LOCK handle locks:
Primary flight controls in neutral. Nosewheel steering via the rudder control system. Throttles in IDLE. All other answers.
What activates the electric aileron trim? Either AILERON TRIM switch. Both AILERON TRIM switches simultaneously. AILERON TRIM HAT on the pilot or copilot flight controls. Manual AILERON TRIM knob on the aft section of the pedestal.
What activates the primary electric elevator trim? Both primary elevator trim switches on either flight control. SECONDARY ELEV TRIM switch on the pedestal. Manual ELEVATOR TRIM Wheel on the left of the special. Both primary elevator trim switches on either flight control or SECONDARY ELEV TRIM switch on the pedestal.
The SECONDARY ELEV TRIM is enabled if: Primary elevator trim is enabled. SECONDARY ELEV TRIM switch is ENABLE. Primary elevator trim circuit breaker is pulled. All other answers.
Where are the trim indicator during normal flight operations? PFD 1. MFD 1 or 2. MFD 2 only. Indicators next to the manual trim knobs.
Where are the flap position indications during normal flight operations? PFD 1 MFD 1 STBY ATTITUDE INDICATOR MFD 1 and STBY ATTITUDE INDICATOR.
What condition(s) command GROUND SPOILERS to extend? Flaps Ground. Power Idle. SPEEDBRAKE handle in GROUND SPOILERS EXTEND with at least 2 squat switches indicating weight on wheels. All other answers.
What does the amber SPEED BRAKES EXTENDED CAS message indicate? Speedbrakes are deployed. Radar altimeter indicates less than 500 feet AGL. Aircraft is not on the ground or in steep approach mode. All other answers.
What does the cyan GROUND SPOILERS EXTENDED CAS message indicate? Ground spoilers fault and the ground spoilers are not deployed. Ground spoilers fault and spoilers are deployed on the ground. Ground spoilers deployed on the ground. Ground spoilers deployed on the ground or in the air.
What does the amber RUDDER BIAS FAIL CAS message indicate? Both rudder bias control valves are in bypass condition, no rudder BIAS. Either rudder bias control valve is in bypass position. Either rudder bias actuator has an imbalance in bleed air pressure. Both rudder bias control valves are in bypass condition, no rudder BIAS and Either rudder bias control valve is in bypass position.
Where is he OXY PSI indication displayed?
PFD Systems. MFD Systems. Gauge located on the left panel. Cabin Management System.
How can the pilot check the crew oxygen system in flight? Don the mask, select OXYGEN MASK switch to MIC and check for airflow. Check the OXY PSI for pressure. Check the OXYGEN CONTROL knob and OXYGEN SUPPLY handle position. All other answers.
What cabin altitude automatically drops the passenger oxygen mask? Approximately 10.000 feet cabin altitude. Approximately 14.800 feet cabin altitude. Approximately 13.150 feet cabin altitude. Between 10.000 and 14.800 feet cabin altitude.
Is it posible to drop the passenger mask at any cabin altitude? Yes – With the OXYGEN CONTROL knob in DROP MASK. Yes – With the OXYGEN SUPPLY handle. No – Mask only drops automatically. Yes – With the OXYGEN CONTROL knob in DROP MASK and With the OXYGEN SUPPLY handle.
What action is required by the passengers to activate the oxygen flow to the passenger mask? The passenger mask has flow as soon as the mask has dropped. The passenger must position the canister in the passenger position to start oxygen flow. The passenger must pull the lanyard to start oxygen flow. The passenger must pull the straps on the mask to start oxygen flow.