B-747 Oral Question Bank & Review (PC)
STUDY GUIDE 2026 COMPLETE QUESTIONS
WITH CORRECT DETAILED ANSWERS ||
100% GUARANTEED PASS <RECENT
VERSION>
1. Q: Describe the primary function of the Flight Management Computer (FMC).
A: The FMC is the core of the aircraft's navigation and performance management
system. It uses a database of navigational aids, routes, and airports, along with aircraft
performance models and pilot inputs, to compute an efficient flight path. It provides
lateral (LNAV) and vertical (VNAV) guidance to the autopilot and flight director, and
calculates key speeds, thrust settings, and altitude constraints.
2. Q: What are the four primary sources of electrical power on the B-747?
A: 1) Four Integrated Drive Generators (IDGs), one on each engine. 2) Auxiliary Power
Unit (APU) generator. 3) External power. 4) Ram Air Turbine (RAT) for emergency power
(deploys automatically or manually).
3. Q: When does the Ram Air Turbine (RAT) deploy automatically?
A: The RAT deploys automatically if both AC BUS 1 and AC BUS 2 are lost (i.e., a complete
electrical failure), or upon detection of a dual hydraulic system failure (Systems 1 & 4). It
provides hydraulic power to flight controls and limited electrical power via a variable
frequency generator.
4. Q: Explain the purpose and basic operation of the Cabin Altitude Control System.
A: This system maintains a safe and comfortable cabin pressure altitude, typically below
8,000 feet, while the aircraft operates at high flight altitudes. It uses outflow valves,
controlled by the cabin pressure controller, to regulate the rate at which air escapes the
cabin. The controller schedules cabin altitude climb and descent based on flight altitude
and pre-programmed landing field elevation.
5. Q: What is the function of the Pack Flow Selector (HIGH, NORM, OFF)?
A: It controls the volume of air supplied by the air conditioning packs. NORM is used for
most operations. HIGH is used for ground operations with high passenger load, during
, smoke removal procedures, or if a pack fails. OFF is used for isolation or in case of a pack
fault/fire.
6. Q: Describe the differences between Primary and Secondary flight controls.
A: Primary controls (Ailerons, Elevators, Rudder) are essential for basic aircraft control
and are hydraulically powered with manual reversion capabilities. Secondary
controls (Flaps, Slats, Spoilers/Speedbrakes, Trim) augment performance for takeoff,
landing, and cruise, and provide lift-dumping or roll augmentation. They are fully power-
actuated.
7. Q: How many hydraulic systems are on the B-747, and what are their primary
designations?
A: There are four independent hydraulic systems: System 1, System 2, System 3, and
System 4. Systems 1 & 4 are the primary flight control systems, while Systems 2 & 3 are
dedicated to utility functions like gear, brakes, and thrust reversers, but can also back up
primary systems.
8. Q: What is the purpose of the Alternate Flap Drive System?
A: It provides a secondary means of extending the flaps using hydraulic system 3
pressure if the normal electrical control or primary hydraulic drive (system 4) fails. It
operates at a slower rate and may have asymmetric protection inhibited.
9. Q: When would you use the Alternate Brake System?
A: The Alternate Brake System is used if the normal power brake system (hydraulic
system 4) is lost or fails. It uses hydraulic system 1 pressure and is controlled by the
alternate brake pedals (on the captain's side) or via auto-brake selector, providing
metered braking pressure.
10. Q: Describe the indication of a successful Engine Driven Pump (EDP) low-pressure
warning.
A: An amber "LOW PRESS" light illuminates on the overhead hydraulic panel for the
respective pump when output pressure drops below a threshold. The associated
pressure indicator will also show low or zero pressure.
11. Q: What does an illuminated FUEL FILTER BYPASS light indicate?
A: It indicates that the fuel filter for that engine is becoming clogged, and differential
pressure across the filter has opened the bypass valve to ensure uninterrupted fuel flow.
Contamination is likely, and the engine fuel filter should be checked at the next
maintenance stop.
, 12. Q: Explain the significance of the "WING BODY OVERHEAT" light.
A: This is a warning of a potential fire or overheat condition in the designated wing or
body bays (e.g., leading edge, trailing edge, wheel well, air conditioning bays). It requires
immediate action per the QRH/ECL checklist, typically involving shutting off associated
pumps, fans, or equipment and discharging fire extinguishers.
13. Q: What is the function of the Cargo Fire Suppression System?
A: It detects and extinguishes fires in the forward and aft cargo compartments. It uses
smoke detectors for warning and a Halon gas suppression agent discharged in two
separate shots to inert the compartment and suppress the fire.
14. Q: How is fire detection and extinguishing accomplished for the engines and APU?
A: Detection: Continuous loop fire/overheat detectors. Extinguishing: Two fire bottles (1
& 2) are available for the engines, with one sufficient to extinguish a fire. The APU has its
own dedicated fire bottle. Discharge is performed from the fire control panel on the
overhead.
15. Q: What does a Master Caution light with an illuminated "FLT CONT" light typically
indicate?
A: It indicates a fault in the primary flight control system, such as a disagreement
between control surfaces and commands, a hydraulic system issue affecting controls, or
a fault in the control surface position sensors. It requires a check of the EICAS memo
messages and appropriate QRH procedures.
16. Q: Describe the purpose of the Standby Power System.
A: It provides essential AC and DC power for critical flight instruments, radios, and some
flight controls if all four main AC buses are lost. It consists of the battery and the Static
Inverter, which converts DC battery power to AC for standby instruments.
17. Q: What is indicated by an EICAS message of "DOOR" in amber?
A: It indicates that one or more doors (passenger, cargo, or access) are not fully closed
and locked. The specific door can be identified on the door synoptic display.
18. Q: When would you activate the Crossfeed Valve(s)?
A: To balance fuel between wings, to feed engines from tanks on the opposite wing in
case of an engine-driven pump failure, or to manage fuel distribution for long-range
center tank usage. They are normally closed for takeoff and landing.
19. Q: What is the role of the Fuel Control Switches (CUTOFF / RUN)?
A: They control the engine fuel shutoff valves. Placing a switch to CUTOFF commands the
STUDY GUIDE 2026 COMPLETE QUESTIONS
WITH CORRECT DETAILED ANSWERS ||
100% GUARANTEED PASS <RECENT
VERSION>
1. Q: Describe the primary function of the Flight Management Computer (FMC).
A: The FMC is the core of the aircraft's navigation and performance management
system. It uses a database of navigational aids, routes, and airports, along with aircraft
performance models and pilot inputs, to compute an efficient flight path. It provides
lateral (LNAV) and vertical (VNAV) guidance to the autopilot and flight director, and
calculates key speeds, thrust settings, and altitude constraints.
2. Q: What are the four primary sources of electrical power on the B-747?
A: 1) Four Integrated Drive Generators (IDGs), one on each engine. 2) Auxiliary Power
Unit (APU) generator. 3) External power. 4) Ram Air Turbine (RAT) for emergency power
(deploys automatically or manually).
3. Q: When does the Ram Air Turbine (RAT) deploy automatically?
A: The RAT deploys automatically if both AC BUS 1 and AC BUS 2 are lost (i.e., a complete
electrical failure), or upon detection of a dual hydraulic system failure (Systems 1 & 4). It
provides hydraulic power to flight controls and limited electrical power via a variable
frequency generator.
4. Q: Explain the purpose and basic operation of the Cabin Altitude Control System.
A: This system maintains a safe and comfortable cabin pressure altitude, typically below
8,000 feet, while the aircraft operates at high flight altitudes. It uses outflow valves,
controlled by the cabin pressure controller, to regulate the rate at which air escapes the
cabin. The controller schedules cabin altitude climb and descent based on flight altitude
and pre-programmed landing field elevation.
5. Q: What is the function of the Pack Flow Selector (HIGH, NORM, OFF)?
A: It controls the volume of air supplied by the air conditioning packs. NORM is used for
most operations. HIGH is used for ground operations with high passenger load, during
, smoke removal procedures, or if a pack fails. OFF is used for isolation or in case of a pack
fault/fire.
6. Q: Describe the differences between Primary and Secondary flight controls.
A: Primary controls (Ailerons, Elevators, Rudder) are essential for basic aircraft control
and are hydraulically powered with manual reversion capabilities. Secondary
controls (Flaps, Slats, Spoilers/Speedbrakes, Trim) augment performance for takeoff,
landing, and cruise, and provide lift-dumping or roll augmentation. They are fully power-
actuated.
7. Q: How many hydraulic systems are on the B-747, and what are their primary
designations?
A: There are four independent hydraulic systems: System 1, System 2, System 3, and
System 4. Systems 1 & 4 are the primary flight control systems, while Systems 2 & 3 are
dedicated to utility functions like gear, brakes, and thrust reversers, but can also back up
primary systems.
8. Q: What is the purpose of the Alternate Flap Drive System?
A: It provides a secondary means of extending the flaps using hydraulic system 3
pressure if the normal electrical control or primary hydraulic drive (system 4) fails. It
operates at a slower rate and may have asymmetric protection inhibited.
9. Q: When would you use the Alternate Brake System?
A: The Alternate Brake System is used if the normal power brake system (hydraulic
system 4) is lost or fails. It uses hydraulic system 1 pressure and is controlled by the
alternate brake pedals (on the captain's side) or via auto-brake selector, providing
metered braking pressure.
10. Q: Describe the indication of a successful Engine Driven Pump (EDP) low-pressure
warning.
A: An amber "LOW PRESS" light illuminates on the overhead hydraulic panel for the
respective pump when output pressure drops below a threshold. The associated
pressure indicator will also show low or zero pressure.
11. Q: What does an illuminated FUEL FILTER BYPASS light indicate?
A: It indicates that the fuel filter for that engine is becoming clogged, and differential
pressure across the filter has opened the bypass valve to ensure uninterrupted fuel flow.
Contamination is likely, and the engine fuel filter should be checked at the next
maintenance stop.
, 12. Q: Explain the significance of the "WING BODY OVERHEAT" light.
A: This is a warning of a potential fire or overheat condition in the designated wing or
body bays (e.g., leading edge, trailing edge, wheel well, air conditioning bays). It requires
immediate action per the QRH/ECL checklist, typically involving shutting off associated
pumps, fans, or equipment and discharging fire extinguishers.
13. Q: What is the function of the Cargo Fire Suppression System?
A: It detects and extinguishes fires in the forward and aft cargo compartments. It uses
smoke detectors for warning and a Halon gas suppression agent discharged in two
separate shots to inert the compartment and suppress the fire.
14. Q: How is fire detection and extinguishing accomplished for the engines and APU?
A: Detection: Continuous loop fire/overheat detectors. Extinguishing: Two fire bottles (1
& 2) are available for the engines, with one sufficient to extinguish a fire. The APU has its
own dedicated fire bottle. Discharge is performed from the fire control panel on the
overhead.
15. Q: What does a Master Caution light with an illuminated "FLT CONT" light typically
indicate?
A: It indicates a fault in the primary flight control system, such as a disagreement
between control surfaces and commands, a hydraulic system issue affecting controls, or
a fault in the control surface position sensors. It requires a check of the EICAS memo
messages and appropriate QRH procedures.
16. Q: Describe the purpose of the Standby Power System.
A: It provides essential AC and DC power for critical flight instruments, radios, and some
flight controls if all four main AC buses are lost. It consists of the battery and the Static
Inverter, which converts DC battery power to AC for standby instruments.
17. Q: What is indicated by an EICAS message of "DOOR" in amber?
A: It indicates that one or more doors (passenger, cargo, or access) are not fully closed
and locked. The specific door can be identified on the door synoptic display.
18. Q: When would you activate the Crossfeed Valve(s)?
A: To balance fuel between wings, to feed engines from tanks on the opposite wing in
case of an engine-driven pump failure, or to manage fuel distribution for long-range
center tank usage. They are normally closed for takeoff and landing.
19. Q: What is the role of the Fuel Control Switches (CUTOFF / RUN)?
A: They control the engine fuel shutoff valves. Placing a switch to CUTOFF commands the
