Flight Operations 2 Flashcards
A bleed leak warning light illuminated in the cockpit could be an indication that there is a:
A) Brake bleed line fluid leak, which could result in a primary brake system failure.
B) Hydraulic air bleed system failure resulting low hydraulic system pressure due to lack of air pressure in the reservoir.
C) Bleed air leak within air cycle compressor and expansion turbine resulting in a pressurization failure.
D) Pneumatic air bleed leak which left unattended could result in a fire within the aircraft.
D) Pneumatic air bleed leak which left unattended could result in a fire within the aircraft.
Which of the following statements best describes an aircraft pressurization system?
A) Bleed air from the engines is continually distributed to the cabin area, outflow valves control the amount of air allowed to escape to obtain the desired level of pressurization.
B) Bleed valves control the amount of bleed air allowed to enter the cabin area to obtain the desired level of pressurization.
C) Ram air is vented into the cabin area utilizing Ram Air Turbines, outflow valves control the amount of air allowed to escape to obtain the desired level of pressurization.
D) Engine driven air cycle packs distribute air to to the cabin area, inflow valves control the amount of air allowed to enter the cabin area to obtain the desired level of pressurization.
A) Bleed air from the engines is continually distributed to the cabin area, outflow valves control the amount of air allowed to escape to obtain the desired level of pressurization.
With respect to aircraft pressurization systems, identify which of the following statements is FALSE?
A) Modern aircraft pressurization systems start to pressurize the cabin during the takeoff run at which time a descent would be noted on the cabin rate of climb/descent indicator.
B) The maximum cabin altitude of a pressurized aircraft should not normally exceed 12,500 FT ASL.
C) During a normal pressurized climb, following takeoff, the cabin rate of climb would be less than the aircraft rate of climb.
D) If during descent the aircraft altitude becomes equal to the cabin altitude, the rate of descent of both the cabin and the aircraft will be the same.
B) The maximum cabin altitude of a pressurized aircraft should not normally exceed 12,500 FT ASL.
What is the purpose of a safety outflow valve on an aircraft pressurization system?
A) To prevent too low a cabin differential pressure from being reached.
B) To vent cabin air overboard when cabin altitude is reached.
C) To prevent ambient air pressure from exceeding cabin pressure.
D) To prevent excessive pressure within the pressure vessel.
D) To prevent excessive pressure within the pressure vessel.
The maximum ratio of cabin air pressure to ambient air pressure that a pressurization system and aircraft pressure vessel can sustain is referred to as_____.
A) Max cabin altitude.
B) Max vessel pressure.
C) Max ambient pressure.
D) Max diff.
D) Max diff.
With respect to aircraft pressurization systems, what is the purpose of a negative pressure relief valve?
A) To prevent the cabin differential pressure from becoming too low.
B) To vent cabin air overboard when cabin altitude is reached.
C) To prevent outside ambient air pressure from exceeding cabin internal pressure.
D) To prevent excessive pressure within the pressure vessel.
C) To prevent outside ambient air pressure from exceeding cabin internal pressure.
The pilot of a small turbojet aircraft cruising at FL330 wishes to descend and land at an airport that is 2,000FT ASL. The cabin altitude of the aircraft is 7,000FT ASL. If the jet descends at a rate of 2,500 FPM, what rate of descent should the pilot set on the cabin rate selector to affect a cabin differential pressure of zero on landing?
A) 500FPM
B) 400FPM
C) 300FPM
D) 200FPM
B) 400FPM
A battery temperature overheat warning on the cockpit advisory panel could be an indication of a:
A) Low battery voltage.
B) High battery voltage.
C) Battery thermal runaway.
D) Ground power failure causing battery depletion.
C) Battery thermal runaway.
What functions do Transformer Rectifier Units (TRUs) and Inverters (INVs) perform on aircraft electrical systems?
A) TRUs are employed to convert direct current to alternating current and INVs are employed to convert alternating current to direct current.
B) TRUs are employed to convert alternating current to direct current and INVs are employed to convert direct current to alternating current.
C) TRUs provide automatic bus fault protection on an aircraft DC system and INVs provide automatic overload protection on an aircrafts AC system.
D) TRUs are employed as voltage regulators in AC systems and INVs are employed as voltage regulators of DC systems.
B) TRUs are employed to convert alternating current to direct current and INVs are employed to convert direct current to alternating current.
An aircrafts bus bar can best be described as:
A) A carefully organized bunch of separate but interconnected circuits which allow important circuits to be isolated or powered by alternate sources in the event of component failure.
B) Multifunctional devices which provide voltage regulation, generator current direction, circuit and generator protection.
C) A system of electrical circuits used to control power fluctuations or surges.
D) A passive system which transfers electrical power between AC and DC powered systems depending on system demand.
A) A carefully organized bunch of separate but interconnected circuits which allow important circuits to be isolated or powered by alternate sources in the event of component failure.
Aircraft electrical circuit protection is provided by which of the following devices:
1) Transformer Rectifier Unit (TRU)
2) Generator Control Unit (GCU)
3) Variable Frequency Generator (AC GEN)
4) Invertor (INV)
5) Circuit Breaker (CB)
6) AC and DC Emergency Busses (EMER BUS)
A) 1, 2, 6.
B) 1, 3, 5.
C) 2, 5.
D) 2, 3, 6.
C) 2, 5.
Many large turbine aircraft employ jet pumps to draw fuel into collector lines in order to ensure the high pressure fuel pump has enough fuel to supply the engine. These jet pumps are activated by:
A) High pressure fuel from the high pressure fuel pump.
B) Electrical boost pumps located in the fuel tanks.
C) The hydromechanical fuel control unit.
D) Direct drive from the engine accessory section.
A) High pressure fuel from the high pressure fuel pump.
Which of the following statements is FALSE with regards to capacitance fuel measurement systems?
A) It remains accurate in all phases of flight.
B) The system measures volume of fuel which is then converted to weight by the FMS computer.
C) Fuel measurement is achieved electrically without the need for moving parts by converting a capacitance measurement to an equivalent fuel measure.
D) Depending upon the aircraft size there may be multiple feel capacitance probes connected in parallel in each tank that assist with an average reading of fuel weight.
B) The system measures volume of fuel which is then converted to weight by the FMS computer.
Magnasticks are fuel quantity measuring devices which:
A) Are located beneath the fuel caps and allow for manual measuring of fuel quantity.
B) Are located in the refueling panel to permit selection of the desired fuel load and automatically shut-off the refueling valves when the desired fuel load is boarded.
C) Are located beneath the wings and allow for manual measuring of fuel quantity.
D) Are located within the fuel tanks and transmit accurate quantity measurement to the fuel quantity gauges in the cockpit.
C) Are located beneath the wings and allow for manual measuring of fuel quantity.
What function(s) are performed by an accumulator on an aircraft hydraulic system?
A) To prevent fluid flow in the event of a serious system leak.
B) To absorb power fluctuations or surges in the system during high system demands and store system pressure to provide backup for key operations in case of a pump failure.
C) Diverts fluid back to the reservoir as system pressure increases beyond a prescribed level.
D) To selectively channel hydraulic fluid to a component or components to accomplish specific tasks.
B) To absorb power fluctuations or surges in the system during high system demands and store system pressure to provide backup for key operations in case of a pump failure.
