1. What are the zones in the aircraft? 100 Lower Half of Fuselage
200 Upper Half of Fuselage.
300 Empennage.
400 Powerplant and Nacelle Struts.
500 Left Wing.
600 Right Wing.
700 Landing Gear and Landing Gear Doors.
800 Doors.
600 Right Wing.
700 Landing Gear and Landing Gear Doors.
800 Doors.
300 Empennage.
400 Powerplant and Nacelle Struts.
500 Left Wing
.
What are the models of B737 NG? B737 NG 600
B737 NG 700
B737 NG 800
B737 NG 900
B737 NG300
B737 NG200
B737 NG400 B737 NG600
B737 NG100
B737 NG800.
What is the body Fuselage station? The main points are wing jacking points A and B and aft body
jacking point C. The four auxiliary points are forward body jacking
point D and three landing gear points E (Nose) and F (Main Landing
Gear).
A vertical plane that is parallel to the
vertical centerline plane, BBL 0.00. It is found by its perpendicular
distance from the fuselage centerline plane. (It is a measurement of
width.
The main circuit breaker panels are behind the first officer and captain.The P6 and P18 have the component load circuit breakers.
Which are the principal and auxiliary points of jacking? The main circuit breaker panels are behind the first officer and captain.The P6 and P18 have the component load circuit breakers. With the loss of normal power, the standby power system supplies a minimum of 30 minutes of AC and DC power to systems The main points are wing jacking points A and B and aft body
jacking point C. The four auxiliary points are forward body jacking
point D and three landing gear points E (Nose) and F (Main Landing
Gear).
.
Where is located p6 and p18 panels? The main circuit breaker panels are behind the first officer and captain.The P6 and P18 have the component load circuit breakers. transforme rectifier unit, convert 115 vac to 28 vdc The external power connector is at the RH side, in the nose of the airplane.
The maximum angle of the nose steering is. 74 degrees 78 degrees 76 degrees.
How many times the standby electrical power system supplies AC and DC power to the electrical network of the aircraft? With the loss of normal power, the standby power system supplies a minimum of 30 minutes of AC and DC power to systems. Provide visual and aural indication to the flight crew A vertical plane that is parallel to the
vertical centerline plane, BBL 0.00. It is found by its perpendicular
distance from the fuselage centerline plane. (It is a measurement of
width.
.
What is the function of TRU? Provide visual and aural indication to the flight crew transforme rectifier unit, convert 115 vac to 28 vdc Transfome rectifier unit,convert 28vdc to 115vac.
. Where is located the external power connection? The external power connector is at the RH side, in the nose of the airplane The P28 APU remote control panel is on the right wheel well aft bulkhead. Provide visual and aural indication to the flight crew.
What is the function of the Static Inverter? The P28 APU remote control panel is on the right wheel well aft bulkhead. Transfome rectifier unit,convert 28vdc to 115vac transforme rectifier unit, convert 115 vac to 28 vdc.
. What type of alert does the Fire and overheat detection system provide to alert the flight crew? Removes oxygen in the center tank air to a level which does not support combustion. The P28 APU remote control panel is on the right wheel well aft bulkhead. Provide visual and aural indication to the flight crew.
Where are located the APU remote control panel? The P28 APU remote control panel is on the right wheel well aft bulkhead. Provide visual and aural indication to the flight crew Transfome rectifier unit,convert 28vdc to 115vac.
What is the function of Nitrogen Generator system? The engine fuel spar valve battery makes sure that the engine fuel feed system always has power to close the engine fuel spar valve. The water scavenge jet pumps remove water from the low points of each tank to prevent corrosion Removes oxygen in the center tank air to a level which does not support combustion.
. How many fuel tanks are installed in the aircraft? These are the fuel tanks:
Main tank 1 (capacity is 8630 lb or 3915 kg).
Main tank 2 (capacity is 8630 lb or 3915 kg).
Center tank (capacity is 28,803 lb or 13,065 kg).
These are the fuel tanks:
Main tank 1 (capacity is 8630 lb or 3812 kg).
Main tank 2 (capacity is 8730 lb or 3915 kg).
Center tank (capacity is 28,503 lb or 13,065 kg).
.
What is the function of the Fuel Spar valve battery The engine fuel spar valve battery makes sure that the engine fuel feed system always has power to close the engine fuel spar valve. the blue valve position lights come on when the refueling shutoff valve solenoids have power The water scavenge jet pumps remove water from the low points of each tank to prevent corrosion.
What is the function of the water scavenge ejector pumps? The engine fuel spar valve battery makes sure that the engine fuel feed system always has power to close the engine fuel spar valve. The water scavenge jet pumps remove water from the low points of each tank to prevent corrosion the blue valve position lights come on when the refueling shutoff valve solenoids have power.
During refueling procedures of the main tanks and center tanks, the BLUE valve sition hts come on? the blue valve position lights come on when the refueling shutoff valve solenoids have power The water scavenge jet pumps remove water from the low points of each tank to prevent corrosion The engine fuel spar valve battery makes sure that the engine fuel feed system always has power to close the engine fuel spar valve.
How may fuel measuring stick are installed in the air craft and what is the function? The main hydraulic systems are A and B. System A has most of its components on the left side of the airplane and system B on the right side and The auxiliary hydraulic systems are the standby hydraulic system. The fuel measuring sticks provide manually measure fuel quantity
There are six measuring sticks in main tank 1 and main tank 2. Each fuel measuring stick is on a fuel tank access door, numbered 3 through 8, from inboards to outboard
There are four fuel tank measuring sticks in the center tank, Two fuel tank measuring sticks are on fuel tank access panels and two are on the wing skin. The center tank fuel measuring sticks are numbered 1 and 2, from inboard to outboard. The inner sticks have graduation marks that show fuel height in linear units.
The hydraulic power transfer unit (PTU) system is an alternate source of hydraulic power for the leading edge flaps and slats and autoslat system, is a hydraulic motor-pump assembly that supplies alternative pressure to leading edge flaps and slats and autoslat system if system B is de-pressurized.
Which are the three main Hydraulic Systems? The main hydraulic systems are A and B. System A has most of its components on the left side of the airplane and system B on the right side and The auxiliary hydraulic systems are the standby hydraulic system. The hydraulic power transfer unit (PTU) system is an alternate source of hydraulic power for the leading edge flaps and slats and autoslat system, is a hydraulic motor-pump assembly that supplies alternative pressure to leading edge flaps and slats and autoslat system if system B is de-pressurized the blue valve position lights come on when the refueling shutoff valve solenoids have power.
What is the function of Power Transfer Unit (PTU)? With the loss of normal power, the standby power system supplies a minimum of 30 minutes of AC and DC power to systems. The hydraulic power transfer unit (PTU) system is an alternate source of hydraulic power for the leading edge flaps and slats and autoslat system, is a hydraulic motor-pump assembly that supplies alternative pressure to leading edge flaps and slats and autoslat system if system B is de-pressurized The main hydraulic systems are A and B. System A has most of its components on the left side of the airplane and system B on the right side and The auxiliary hydraulic systems are the standby hydraulic system.
1. Where is the main cabin pressurization outflow valve located? RH aft fuselage Passenger cabin,Lavatories,Galleys. The parking brake system.
Which zone in the B737-600/700 aircraft are temperature controlled by the Air Conditioning System? Stage 5 IPC and Stage 9 HPC. Passenger cabin,Lavatories,Galleys. Exhaust Gas Temperature.
What is the function of the main gear torsion link? The torsion links prevent the inner shock strut from rotation in the outer shock strut. The main gear shimmy damper decreases vibration between the inner and outer cylinders during high speed taxi and heavy brake use. The parking brake system. .
What does it mean when the GREEN, RED landing gear position lights come on and when all landing gear position lights are off? Green light landing gear is down and everything is secure.
Red light is in transition that the landing gear is moving.
Landing gear is up and made sure all lights are off.
Black light landing gear is down and everything is secure.
Red light is in transition that the landing gear is moving.
Yelow gear is up and made sure all lights are off.
Green light landing gear is down and everything is secure.
Ocher light is in transition that the landing gear is moving.
Landing gear is up and made sure all lights are off.
.
What is the function of Shimmy damper? The parking brake system The main gear shimmy damper decreases vibration between the inner and outer cylinders during high speed taxi and heavy brake use. The torsion links prevent the inner shock strut from rotation in the outer shock strut.
6. What brake system gets pressure to operate the brakes to stops wheel rotation before the landing gear retracts? The parking brake system Passenger cabin,Lavatories,Galleys. Exhaust Gas Temperature.
What are the sources of the Pneumatic system? Engine 1 bleed air system
Engine 2 bleed air system
Auxiliary power unit (APU) bleed air system
Pneumatic ground air connection
Engine 2 bleed air system
Engine 3bleed air system
Auxiliary power unit (APU) bleed air system
Pneumatic ground air system
.
What the stages of the engine is used to obtain the bleed air to the pneumatic system? Stage 5 IPC and Stage 9 HPC. Stage 6 IPC and Stage 8 HPC. Stage 4 IPC and Stage 7HPC.
What is the meaning of EGT? Stage 5 IPC and Stage 9 HPC Temperature Exhaust Gas Exhaust Gas Temperature.
What are the incorrect conditions for which the ECU performs a protective shutdown of the APU? The EPU energizes the flow divider solenoid closed from 7 percent to 30 percent speed. This prevents APU flame out and shutdown during a start
Low oil pressure, high oil temperature or starter- generator filter clogged causes the ECU to do a protective shutdown when the APU is above 95 percent speed
The ECU energizes the flow divider solenoid closed from 7 percent to 30 percent speed. This prevents APU flame out and shutdown during a start
Low oil pressure, high oil temperature or starter- generator filter clogged causes the ECU to do a protective shutdown when the APU is above 95 percent speed
The EPC energizes the flow divider solenoid closed from 7 percent to 30 percent speed. This prevents APU flame out and shutdown during a start
Low oil pressure, high oil temperature or starter- generator filter clogged causes the ECU to do a protective shutdown when the APU is above 95 percent speed
.
How many Thermocouples are installed in the APU? Two thermocouples three thermocouples Four thermocouples.
What are the primary flight control? Aileron (2), Rudder, Elevator (2). Ailron(2),stabilizer(2) and Rudder Elevator,Flaps and rudder.
What are the secondary flight control? Leading edge devices (12), Trailing edge flaps (4), Spoilers and Speedbrakes (12), Horizontal Stabilizer. Leading edge devices (10), Trailing edge flaps (3), Spoilers and Speedbrakes (11), Horizontal Stabilizer. Leading edge devices (9), Trailing edge flaps (5), Spoilers and Speedbrakes (8), Horizontal Stabilizer.
What is the purpose of flight spoilers? Manual Operated – Stabilizer Trim Wheels, Electric Operation – Stabilizer Trim Switches, Autopilot Operation.
The flight spoilers help the ailerons control airplane roll around the longitudinal axis. They also supply speedbrake control to decrease lift and increase drag during landing and refused takeoff. During roll control the flight spoilers on one wing move up, and all the other spoilers stay down. The ECU energizes the flow divider solenoid closed from 7 percent to 30 percent speed. This prevents APU flame out and shutdown during a start
Low oil pressure, high oil temperature or starter- generator filter clogged causes the ECU to do a protective shutdown when the APU is above 95 percent speed
.
How the horizontal Stabilizer is operated? Manual Operated – Stabilizer Trim Wheels, Electric Operation – Stabilizer Trim Switches, Autopilot Operation. LEADING EDGE FLAP AND SLAT.
How is operated the Leading edge flap and slat and the Trailing edge Flaps in a Standby condition? LEADING EDGE FLAP AND SLAT:
Normal Operation
During the normal operation, use the flap lever to operate the LE flaps and slats. System B hydraulic power is necessary for normal operation.
Alternate Operation
When you move the alternate flaps arm switch to the arm position, electrical power becomes available to the alternate flaps control switch.
The arm switch supplies signals to the standby hydraulic system to operate the standby hydraulic electric motor driven pump (EMDP)
TRAILING EDGE FLAPS:
Normal Operation
The flap lever moves a cable system that supplies a mechanical input to the flap control valve through the flap control unit.
Alternate Operation
The alternate flaps control switch operates only when the alternate flaps arm switch is in the arm position.
The flight spoilers help the ailerons control airplane roll around the longitudinal axis. They also supply speedbrake control to decrease lift and increase drag during landing and refused takeoff. During roll control the flight spoilers on one wing move up, and all the other spoilers stay down. The main gear shimmy damper decreases vibration between the inner and outer cylinders during high speed taxi and heavy brake use.
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