A320 Review United Exam Questions and Answers 100% Pass |Verified and Updated |Graded A+

A320 Review United
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1. The potable water system is pressurized by
A. The hydraulic system
B. Ambient air pressure
C. The pneumatic system
D. The PTU

Airplane General/Emergency Equipment: C. The pneumatic system
2. FASTEN SEAT BELT and RETURN TO YOUR SEAT signs illuminate when cabin
altitude exceeds ________ feet, regardless of switch position.
A. 10,000 B. 11,300 C. 13,500 D. 14,000

Airplane General/Emergency Equipment: B. 11,300
3. NO SMOKING and EXIT signs illuminate when cabin altitude exceeds ________
feet, regardless of switch position.
A. 10,000 B. 11,300 C. 13,500 D. 14,000

Airplane General/Emergency Equipment: B. 11,300
4. In the AUTO position, the NO SMOKING switch causes the
A. NO SMOKING lights to extinguish on the ground with engines shutdown.
B. NO SMOKING and EXIT signs to illuminate with flap extension
C. NO SMOKING signs to extinguish at the gate when external power connected
is connected
D. NO SMOKING and EXIT signs to illuminate when landing gear is extended,
and extinguish when landing gear is retracted.

Airplane General/Emergency Equipment: D. NO SMOKING and EXIT signs to illuminate when
landing gear is extended, and extinguish when landing gear is retracted.
5. If normal electrical power is lost, the following lights remain available:
A. Captain's instrument panel (powered CRTs and flood lighting)
B. Map and utility lights for chart holder C. Side console, floor, and flight bag
storage lighting
D. Both dome lights



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Airplane General/Emergency Equipment: A.Captain's instrument panel (powered CRTs and flood
lighting)
6. What is the normal in-flight position of the red tab N/100% PUSH Switch on
the oxygen mask?
A. Either N or 100% is acceptable.
B. N position below 35,000 ft. and 100% above.
C. N position.
D. 100%.

Airplane General/Emergency Equipment: D. 100%.
7. If the Emergency Access code is entered on Flight Deck Access Panel and no
cockpit action is taken when will the cockpit door automatically unlock?
A. 10 seconds.
B. 20 seconds.
C. 30 seconds.
D. 40 seconds.

Airplane General/Emergency Equipment: C. 30 seconds
8. Galleys are powered by
A. DC Battery Bus.
B. AC and DC Shed busses. C. DCBus1and2.
D. Both Main AC Busses.

Airplane General/Emergency Equipment: D. Both Main AC Busses.
9. Cargo door operation is normally powered by the
A. Green hydraulic system.
B. Blue hydraulic system.
C. Yellow electric hydraulic pump.
D. Green system through the PTU.

Airplane General/Emergency Equipment: C. Yellow electric hydraulic pump.




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10. The aircraft passenger WIFI system can be powered OFF by
A. Battery Bus switches.
B. GALLEY or GALLEY & CAB switch.
C. Turning OFF the BUS TIE switch.
D. GEN 1 SMOKE light switch.

Airplane General/Emergency Equipment: B. GALLEY or GALLEY & CAB switch.
11. Air for the pneumatic system is normally bled from the ____ of the compres-
sor.
A. Intermediate pressure stage
B. High pressure stage
C. Low pressure stage
D. Fan stage air: A. Intermediate pressure stage
12. What happens in flight if pneumatic bleed air pressure is insufficient even
with the HP stage valve open?
A. APU starts automatically.
B. Engines spool up automatically.
C. Outflow valve closes automatically.
D. Packs automatically go to low flow.: B. Engines spool up automatically.
13. What valve action automatically occurs when the APU supplies air to the
pneumatic system?
A. Crossbleed valve opens and the engine bleed valves close.
B. Crossbleed valve closes and the engine bleed valves open.
C. Crossbleed valve closes and the engine bleed valves close
D. Crossbleed valve opens and the engine bleed valves open.: A. Crossbleed valve opens
and the engine bleed valves close.
14. Pneumatic system operation is controlled and monitored by
A. An Avionics Equipment Ventilation Computer (AEVC). B. Two Cabin Pressure
Controllers (CPCs).
C. An Electronic Control Box (ECB).
D. Two Bleed Monitoring Computers (BMCs).: D. Two Bleed Monitoring Computers (BMCs).



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15. If BMC 1 fails, what leak detection is lost?
A. Engine 1 & 2.
B. Engine 2 & APU.
C. Engine 1, 2, & APU.
D. Engine 1 & APU.: D. Engine 1 & APU.
16. If BMC 2 fails, what leak detection is lost?
A. Engine 1 & 2.
B. Engine 2 & APU.
C. Engine 1, 2, & APU.
D. Engine 2.: D. Engine 2.
17. A blue item on the takeoff memo indicates a checklist item that is
A. To be accomplished. B. Complete.
C. Faulted.
D. In a test subroutine.: A. To be accomplished.
18. A cavalry charge aural signal indicates a(an)
A. Level 3 ECAM B. Autopilot disconnect C. Altitude alert D. Overspeed: B. Autopilot
disconnect
19. A triple click aural sound indicates
A. Level 1 ECAM. B. Flight attendant call C. Altitude alert. D. Landing capability
change: D. Landing capability change
20. What does the green arrow on the memo section of the E/WD indicate?
A. Overflow information on the SD B. Overflow information on the STS page C.
More than one page of alert messages is available for display on the E/WD D.
Additional information on the ND.: C. More than one page of alert messages is available for display
on the E/WD
21. T.O. INHIBIT is active
A. From takeoff power application to 1500 feet AGL, or for two minutes after
takeoff. B. From takeoff power application to 3000 feet AGL, or for three min-
utes after takeoff. C. After engine start. D. When slats are extended.: A. From takeoff
power application to 1500 feet AGL, or for two minutes after takeoff
22. What is the function of the T.O. INHIBIT?
A. Verifies correct takeoff configuration B. Prevents takeoff with unsafe config-