B737 Engine & APU - TS Flashcards
Still in progress, comments welcomed... (59 cards)
0
Q
- The 700/800/900 APU generator will supply both Transfer buses in flight
A
TRUE
1
Q
- What electrical power source is required for starting the APU?
A
Aircraft battery
2
Q
- What is the fuel source for starting the APU with only aircraft battery power available? (COLD aircraft)
A
1 fuel tank
3
Q
- A 737-800 aircraft is in-flight with APU running. Turning OFF the aircraft BATTERY switch will
A
Cause the APU to shut down
4
Q
- What are the initial indications when the APU is starting?
A
LOW OIL PRESSURE light one, full scale negative amps indication on DC ammeter BAT position
5
Q
- The New Generation 737 APU generator can be used to supply both Transfer Buses up to what maximum altitude?
A
41,000 feet if no APU bleed air is used
6
Q
- What does an illuminated APU MAINT light indicate?
A
Oil quantity is insufficient for extended operation
7
Q
- What prevents the APU electrical and bleed air loads from increasing the EGT above acceptable levels?
A
The APU bleed valve modulates toward the closed position
8
Q
- What indicates the APU generator is ready for use?
A
When the blue APU GEN OFF BUS light illuminates
9
Q
- What is the normal procedure for using APU bleed air after starting the APU?
A
APU bleed air switch may be turned ON after one full minute of APU operation
10
Q
- What causes an automatic shutdown of the APU?
A
Fire warning
11
Q
- What causes an automatic shutdown of the APU in flight?
A
BAT switch placed to OFF
12
Q
- Which of the following causes an automatic shutdown of the APU in flight or on the ground?
A
Fire warning
13
Q
- Which sequence of events should be accomplished for normal shutdown of the APU when “securing” the airplane?
A
Operate for one minute with no pneumatic load, place APU switch to OFF, wait 120 seconds, then battery switch OFF
14
Q
- Which of the following set of conditions causes the APU OVERSPEED light to illuminate?
A
All answers are correct: APU start abort, APU speed sensing failed-APU shuts down, APU rpm limit exceeded
15
Q
- A normal APU start cycle can take as long as:
A
120 seconds
16
Q
- Inflight, with one engine generator inoperative, the APU can supply electrical power to:
A
both buses up to 41,000 feet
17
Q
- A 737-700 aircraft is parked with APU running. Turning the APU control switch to OFF __________.
A
All answers are correct: closes the APU bleed valve, trips the APU generator field relay, shuts down the APU after 60 sec
18
Q
- An illuminated APU “GEN OFF BUS” light indicates:
A
The APU is at operating speed
19
Q
- Turning the battery switch to OFF inflight, will cause the APU to shut down
A
TRUE
20
Q
- Minimum battery voltage for APU start is:
A
23 volts
21
Q
- APU starter engagement may first be observed by:
A
Full scale left deflection of DC ammeter with the BAT position selected
22
Q
- After APU shutdown, the battery switch should remain on for 120 seconds after the APU switch has been placed to OFF.
A
TRUE
23
Q
- What causes an APU OVERSPEED annunciator light to illuminate?
A
All of these answers are correct: APU rpm exceeds limits, APU auto start sequence is aborted, over speed shutdown protection is inop during APU shutdown
24
25. An illuminated APU DET INOP light when no fire warning test is being performed:
Requires the APU to be shut down if operating because the detectors is inop
25
26. After an inflight APU start, the APU will supply ___________.
Pneumatic load only up to 17,000 feet
26
27. The maximum allowable EGT for the APU is ______.
There is none
27
28. After aborting an APU start, how soon may another start be attempted?
After 3rd attempt 15 minutes
28
29. Successful APU starts are not assured above ___________.
FL 250
29
30. What is the primary function of the Main Engine Control?
Hydro-mechanical control of fuel
30
31. What is the automatic function of the EEC during a climb?
Maintain initial N1 climb thrust throughout climb
31
32. When is Engine speed commanded to LOW IDLE?
On the ground, four seconds after touchdown
32
33. How is the main fuel shutoff valve at the engine pylon operated?
Electrical control by the engine start lever and fire switch
33
34. A dim FUEL VALVE CLOSED light indicates?
Main fuel shutoff valve at the engine pylon is closed
34
35. What does an illuminated fuel FILTER BYPASS light indicate?
Impending bypass of the engine fuel filter
35
36. How is the HMU fuel shutoff valve operated? (This valve is at the engine fuel control)
Electrically by the engine fire warning switch and start lever
36
37. What does the engine oil pressure indicator show?
Unregulated pressure as a function of N2 speed
37
38. What is indicated when the OIL FILTER BYPASS light illuminates?
The scavenge oil filter is contaminated
38
39. The engine oil temperature indicator shows oil temperature coming out of the engine after the oil cooler
TRUE
39
40. During engine start, the start switch disengages at N2.
56%
40
41. The _______shows the current mode of the N1 limit computed by the FMC.
Thrust Mode Annunciator
41
42. The engine accessory components are driven by
The N2 spool
42
43. With the engine at normal operating temperature and idle, the oil PRESSURE must be ___________.
Above the red radial
43
44. Engine fan air cools _______.
The IDG/Generator
44
45. With the engine at climb N1 limit power, the stage pneumatic bleed provides bleed air for the pneumatic system.
5th
45
46. The power to move the engine thrust reversers is ______.
Hydraulic
46
47. Engine oil is cooled by ___________.
Engine fuel flow
47
48. Reverse thrust operation is permitted for
Ground use only
48
49. What is maximum engine N1 limit?
104.0%
49
50. What is maximum engine N2?
1 05.0%
50
51. What is maximum takeoff EGT?
950 C
51
52. What is maximum continuous engine EGT?
925C
52
53. What is maximum starting EGT for the aircraft engines?
725C
53
54. What is minimum oil pressure for continued engine operation?
13 psi
54
55. An engine must be shut down if the oil temperature exceeds __________.
155C
55
56. Which is the correct EEC switch configuration for takeoff?
Both must be ON or both ALT
56
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?
Place the APU switch to OFF, then try again
57
58. What causes an automatic shutdown of the APU inflight?
LOW OIL PRESS light on
58
59. The New Generation aircraft APU generator will power both transfer buses inflight.
a. True
