B737 System Validation Question Bank - Engines & Apu R1

Front 1

1. What electrical power source is required for starting the APU?
a. Aircraft battery
b. External AC
c. AC Ground service bus

Back 1

a. Aircraft battery

Front 2

2. The 700/800/900 APU generator will supply both Transfer buses in flight
a. True
b. False

Back 2

a. True

Front 3

3. What is the fuel source for starting the APU with only aircraft battery power available? (COLD aircraft)
a. Center fuel tank with crossfeed open
b. #1 fuel tank
c. #2 fuel tank with crossfeed valve OPEN

Back 3

b. #1 fuel tank

Front 4

4. A 737-800 aircraft is in-flight with APU running. Turning OFF the aircraft BATTERY switch will?
a. Cause the APU to shut down
b. Have no effect on the APU

Back 4

a. Cause the APU to shut down

Front 5

5. What are the initial indications when the APU is starting?
a. LOW OIL PRESSURE light on, full scale negative amps & volts indication on DC meters BAT position
b. LOW OIL PRESSURE light on, full scale positive amps indication of DC ammeter BAT position
c. LOW OIL PRESSURE light one, full scale negative amps indication on DC ammeter BAT position

Back 5

c. LOW OIL PRESSURE light one, full scale negative amps indication on DC ammeter BAT position

Front 6

6. The New Generation 737 APU generator can be used to supply both Transfer Buses up to what maximum altitude?
a. 14,000 feet if the APU is running both Transfer Buses and both packs
b. 17,000 feet if the APU is also used for one pack
c. 41,000 feet if no APU bleed air is used

Back 6

c. 41,000 feet if no APU bleed air is used

Front 7

7. What does an illuminated APU MAINT light indicate?
a. Oil quantity is insufficient for extended operation
b. Crew must shut down APU immediately when light comes on
c. The APU shuts down automatically after 90 seconds

Back 7

a. Oil quantity is insufficient for extended operation

Front 8

8. What prevents the APU electrical and bleed air loads from increasing the EGT above acceptable levels?
a. The APU automatically shuts down
b. The APU fuel control reduces fuel flow
c. The APU bleed valve modulates toward the closed position
d. The APU generator breaker automatically opens

Back 8

c. The APU bleed valve modulates toward the closed position

Front 9

9. What indicates the APU generator is ready for use?
a. When the APU ammeter shows a positive indication
b. When the blue APU GEN OFF BUS light illuminates
c. When the blue APU GEN OFF BUS light is out

Back 9

b. When the blue APU GEN OFF BUS light illuminates

Front 10

10. What is the normal procedure for using APU bleed air after starting the APU?
a. The APU bleed valve will automatically open when bleed air pressure is indicated
b. APU bleed air switch may be turned ON after one full minute of APU operation
c. APU bleed air switch may be turned ON as soon as the APU GEN OFF BUS light comes on

Back 10

b. APU bleed air switch may be turned ON after one full minute of APU operation

Front 11

11. What causes an automatic shutdown of the APU?
a. APU EGT over temperature
b. Fire warning
c. High oil pressure

Back 11

b. Fire warning

Front 12

12. What causes an automatic shutdown of the APU in flight? (NG 700)
a. BAT switch placed to OFF
b. High oil pressure
c. High EGT

Back 12

a. BAT switch placed to OFF

Front 13

13. Which of the following causes an automatic shutdown of the APU in flight or on the ground?
a. EGT overtemperature
b. High oil pressure
c. Fire warning

Back 13

c. Fire warning

Front 14

14. Which sequence of events should be accomplished for normal shutdown of the APU when “securing” the airplane?
a. Operate for 20 seconds with no pneumatic load, then place APU and battery switches to OFF
b. Operate for 30 seconds with no pneumatic load, then place APU switch to OFF
c. Operate for one minute with no pneumatic load, place APU switch to OFF, wait 20 seconds, then battery switch OFF

Back 14

c. Operate for one minute with no pneumatic load, place APU switch to OFF, wait 20 seconds, then battery switch OFF

Front 15

15. Which of the following set of conditions causes the APU OVERSPEED light to illuminate?
a. APU start aborted
b. APU speed sensing has failed and the APU is shutdown
c. APU rpm limit exceeded
d. All answers are correct

Back 15

d. All answers are correct

Front 16

16. A normal APU start cycle can take as long as:
a. 60 seconds
b. 90 seconds
c. 135 seconds

Back 16

c. 135 seconds

Front 17

17. Inflight, with one engine generator inoperative, the APU can supply electrical power to: (300/500)
a. One bus and one pack up to 17,000 feet
b. One bus up to 35,000 feet
c. One bus up to 37,000 feet
d. Both busses if the APU bleed valve is closed

Back 17

b. One bus up to 35,000 feet

Front 18

18. A 737-700 aircraft is parked with APU running. Turning the APU control switch to OFF __________.
a. Closes the APU bleed valve
b. Trips the APU generator field relay
c. Shuts down the APU after 60 seconds
d. All answers are correct

Back 18

d. All answers are correct

Front 19

19. An illuminated APU “GEN OFF BUS” light indicates:
a. The APU is powering bus #1
b. The APU is powering bus #2
c. The APU is powering both bus #1 and #2
d. The APU is at operating speed

Back 19

d. The APU is at operating speed

Front 20

20. Turning the battery switch to OFF inflight, will cause the APU to shut down. (300/500)
a. True
b. False

Back 20

b. False

Front 21

21. Minimum batter voltage for APU start is:
a. 18 volts
b. 22 volts
c. 23 volts
d. 24 volts

Back 21

c. 23 volts

Front 22

22. APU starter engagement may first be observed by:
a. APU “oil pressure low” light illumination and extinguishing
b. APU “gen off bus” light extinguishing
c. AC frequency meter with AC meters selector in the INV position
d. Full scale left deflection of DC ammeter with the BAT position selected

Back 22

d. Full scale left deflection of DC ammeter with the BAT position selected

Front 23

23. After APU shutdown, the battery switch should remain on for 20 seconds after the APU switch has been placed to OFF.
a. True
b. False

Back 23

a. True

Front 24

24. What causes an APU OVERSPEED annunciator light to illuminate?
a. Overspeed shutdown protection is inoperative during APU shutdown
b. APU automatic start sequence is aborted
c. APU rpm exceeds limits
d. All of these answers are correct

Back 24

d. All of these answers are correct

Front 25

25. An illuminated APU DET INOP light when no fire warning test is being performed:
a. Requires the APU to be shut down if operating because the detectors is inop
b. Causes the APU to shutdown automatically
c. Indicates that the faulty detector has been deselected, and that all APU fire warning capability is functional

Back 25

a. Requires the APU to be shut down if operating because the detectors is inop

Front 26

26. After an inflight APU start, the APU will supply ___________. (300/500)
a. Pneumatic load only up to 17,000 feet
b. Pneumatic and electric power up to 17,000 feet
c. Both generator busses inflight up to 37,000 feet

Back 26

a. Pneumatic load only up to 17,000 feet

Front 27

27. The maximum allowable EGT for the APU is ______. (300/500)
a. 610 degrees C max continuous, 677 degrees C maximum
b. 700 degrees C maximum start, 670 degrees C max continuous
c. 725 degrees C start, 700 degrees C max continuous
d. 760 degrees C maximum, 700 degrees C max continuous

Back 27

d. 760 degrees C maximum, 700 degrees C max continuous

Front 28

28. After aborting an APU start, how soon may another start be attempted?
a. Immediately
b. After 4 minutes
c. After 4 minutes on the ground, after 2 minutes in flight
d. Below 300 degrees C EGT

Back 28

b. After 4 minutes

Front 29

29. Successful APU starts are not assured above ___________.
a. FL 250
b. FL 280
c. FL 310
d. FL 350

Back 29

a. FL 250

Front 30

30. What is the primary function of the Main Engine Control?
a. Direct electronic control of N1 speed
b. Electronic override of the PMS
c. Hydro-mechanical control of fuel

Back 30

c. Hydro-mechanical control of fuel

Front 31

31. What is the automatic function of the PMC during a climb?
a. Maintain initial N1 climb thrust throughout climb
b. Maintain constant EGT during climbs
c. Maintain constant fuel flow at all altitudes

Back 31

a. Maintain initial N1 climb thrust throughout climb

Front 32

32. When is Engine speed commanded to LOW IDLE?
a. Flaps extend to 15 or more
b. On the ground, four seconds after touchdown
c. Cowl anti-ice turned on

Back 32

b. On the ground, four seconds after touchdown

Front 33

33. How is the main fuel shutoff valve at the engine pylon operated?
a. Mechanical control by the start lever and engine fire switch
b. Fuel boost pump pressure control initiated by the engine start lever and fire switch
c. Electrical control by the engine start lever and fire switch

Back 33

c. Electrical control by the engine start lever and fire switch

Front 34

34. A dim FUEL VALVE CLOSED light indicates?
a. Engine fuel control shutoff valve (MEC valve) is closed
b. Main fuel shutoff valve at the engine pylon is closed
c. Main fuel shutoff valve at the engine pylon position disagreement

Back 34

b. Main fuel shutoff valve at the engine pylon is closed

Front 35

35. What does an illuminated fuel FILTER BYPASS light indicate?
a. First stage engine driven fuel pump failure
b. Impending bypass of the engine fuel filter
c. Impending fuel bypass through the servo fuel heater

Back 35

b. Impending bypass of the engine fuel filter

Front 36

36. How is the Main Engine control (MEC) fuel shutoff valve operated? (This valve is at the engine fuel control)
a. Mechanically by the engine start lever
b. Electrically by the engine fire warning switch
c. 1st stage engine fuel pump pressure and start switch

Back 36

a. Mechanically by the engine start lever

Front 37

37. What does the engine oil pressure indicator show?
a. Normal regulated pressure from 40 55 psi
b. Regulated pressure for all flight conditions
c. Unregulated pressure as a function of N2 speed

Back 37

c. Unregulated pressure as a function of N2 speed

Front 38

38. What is indicated when the OIL FILTER BYPASS light illuminates?
a. The scavenge oil filter is contaminated
b. The fuel/oil heat exchanger is contaminated
c. The oil is bypassing the fuel/oil heat exchanger

Back 38

a. The scavenge oil filter is contaminated

Front 39

39. The engine oil temperature indicator shows oil temperature coming out of the engine prior to the oil cooler
a. True
b. False

Back 39

a. True

Front 40

40. During engine start, the start switch disengages at N2. (500)
a. 25%
b. 46%
c. 50%
d. 56%

Back 40

b. 46%

Front 41

41. The _______shows the current mode of the N1 limit computed by the FMC.
a. PMI
b. Thrust Rating Indicator
c. Thrust Rating Computer
d. Thrust Mode Annunciator

Back 41

d. Thrust Mode Annunciator

Front 42

42. The engine accessory components are driven by
a. The N1 spool
b. The N2 spool
c. Both N1 & N2 spools
d. The Constant Speed Drive

Back 42

b. The N2 spool

Front 43

43. With the engine at normal operating temperature and idle, the oil PRESSURE must be ___________.
a. In the green band
b. 55 psi or more
c. Above the red radial

Back 43

c. Above the red radial

Front 44

44. Engine fan air cools _______. (300/500)
a. The Trim Air
b. The air conditioning pack
c. The CSD/Generator
d. The air conditioning heat exchanger

Back 44

c. The CSD/Generator

Front 45

45. With the engine at climb N1 limit power, the stage pneumatic bleed provides bleed air for the pneumatic system.
a. 5th
b. 6th
c. 8th
d. 9th

Back 45

a. 5th

Front 46

46. The power to move the engine thrust reversers is ______.
a. Pneumatic
b. Electric
c. Hydraulic

Back 46

c. Hydraulic

Front 47

47. Engine oil is cooled by ___________.
a. Engine fan air
b. Engine fuel flow
c. The left pack
d. Ram air

Back 47

b. Engine fuel flow

Front 48

48. Reverse thrust operation is permitted for
a. Power-back
b. Slowing the aircraft during the descent
c. Ground use only

Back 48

c. Ground use only

Front 49

49. What is maximum engine N1 limit?
a. 106%
b. 105%
c. 100%

Back 49

a. 106%

Front 50

50. What is maximum engine N2?
a. 106%
b. 105%
c. 100%

Back 50

b. 105%

Front 51

51. What is maximum takeoff EGT?
a. 930 C
b. 900C
c. 760 C

Back 51

a. 930 C

Front 52

52. What is maximum continuous engine EGT?
a. Red line
b. 895C
c. 890C

Back 52

b. 895C

Front 53

53. What is maximum starting EGT for the aircraft engines?
a. 760 C
b. 725C
c. 710 C

Back 53

b. 725C

Front 54

54. What is minimum oil pressure for continued engine operation?
a. 13 psi
b. 20 psi
c. 45 psi
d. 55 psi

Back 54

a. 13 psi

Front 55

55. An engine must be shut down if the oil temperature exceeds __________.
a. 165 C
b. 160 C
c. 125 C

Back 55

a. 165 C

Front 56

56. Which is the correct PMC switch configuration for takeoff?
a. Both must be ON or both INOP (OFF)
b. One may be INOP (OFF)
c. #1 must be operative, but #2 may be INOP

Back 56

a. Both must be ON or both INOP (OFF)

Front 57

57. Condition: BAT Volts: 23V; BATT SW: ON; APU SW placed to START; no DC ammeter deflection is observed during a one minute period. What should the pilot do?
a. Place the APU switch to OFF for 20 seconds, then try again
b. Place the APU switch to OFF for 120 seconds, then try again
c. Call Maintenance
d. Leave the aircraft and head to the bar for a drink!

Back 57

a. Place the APU switch to OFF for 20 seconds, then try again

Front 58

58. What causes an automatic shutdown of the APU inflight?
a. LOW OIL PRESS light on
a. HIGH OIL PRESS light on
a. LOW OIL TEMP light on
a. MAINT light on

Back 58

a. LOW OIL PRESS light on

Front 59

59. The New Generation aircraft APU generator will power both transfer buses inflight.
a. True
b. False
c. Don't have a clue
d. Don't care - as long as I'm fying a NG and not a 500!

Back 59

a. a. True

Front 60

These Cards are not verified accurate. Please, If you find a mistake, email: [e-mail]

Back 60

Check back for future revisions!