CFM56-7B Advanced Engine Systems Test 4

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CFM56-7B Advanced Engine Systems Test 4

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cfm
The Power
Of Flightcfm
The Power
Of Flight
Name:
Date:

 Class Number:

 Correct Answers:

Directions: For each of the following questions, circle the letter that is the most correct answer.

1. Inside the fuel assembly there are ____ pump(s) and _____ shaft(s). (3.D.c)
A. __3__ pumps and ___2__ shafts
B. __1__ pumps and ___1__ shafts
C. __2__ pumps and ___2__ shafts
D. __2__ pumps and ___3__ shafts
2. The IDG fuel to oil cooler or heat exchanger, is in series with the ___________ to cool the IDG oil. (3.D.c)
A. IDG servo fuel heater found in ATA chapter 72-00-00,
B. IDG air/fuel cooler found in ATA chapter 71-00-00,
C. IDG fuel/oil cooler found in ATA chapter 73-00-00,
D. IDG air/oil cooler found in ATA chapter 24-00-00,
3. The EEC controls the Burner staging valve by: (3.D.c)
A. an EHSV in the HMU sending an electrical signal to open or close the BSV.
B. an EHSV in the HMU sending an servo signal to open or close the BSV.
C. a solenoid in the HMU sending a servo signal to open or close the BSV.
D. a solenoid in the HMU sending an electrical signal to open or close the BSV.
4. The operation of the servo fuel heater is to. (2.C.b)
A. To prevent hot oil temperatures in the IDG cooling system.
B. To help cool the engine fuel into the fuel nozzles.
C. To direct oil, fuel, hydraulic fluid, water and vapor overboard.
D. To prevent ice in the servo systems.
5. The fuel nozzle shrouds on the fuel manifold___ (3.D.c)
A. To prevent oil contact with hot engine areas by enclosing and sealing of the fuel nozzle B-nut connection .
B. To prevent fuel contact with hot engine areas by enclosing and sealing of the fuel nozzle B-nut connection .
C. allows a leaking fuel nozzle B-nut connection to drain overboard through a drain line.
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D. To prevent fuel contact with fan areas of the fuel nozzle B-nut connection .
July 2004
Test 4

CFM56-7B Advanced Engine Systems Test 4

6. The EEC switches for the CFM56-7 engine will display a amber ALTN in the flight compartment when. (3.D.c)
A. Pressure total is no loner valid from both ADIRU's.
B. the PT25 sensor is no loner valid from both ADIRU's.
C. the PT25 sensor is no loner valid.
D. Pressure total is no loner valid from either of the ADIRU's.
7. The ENGINE CONTROL light is to alert the flight crew that (3.D.c)
A. a flame out has happened in flight
B. the engine has failed
C. a no dispatch condition alert on the ground for the flight crew
D. a no dispatch condition alert on the ground and in flight, for the flight crew
8. How is the engine serial number changed in the CDU for CFM56-7 engine if another one is installed? (3.D.c)
A. You change the metal engine data plate near the oil tank.
B. The serial number is read directly from the ID plug.
C. It can not be changed except by the FAA.
D. The technician is required to change it through the CDU.
9. The N1 trim modifier is in the ID plug of the engine to down trim N1 RPM if necessary, but is; (3.D.c)
A. not used once the aircraft is in flight
B. invalid till the aircraft is in flight.
C. inhibited above 15,500 feet and or Mach number is above .45.
D. not inhibited above 15,500 feet and or Mach number is above .45.
10. The EEC alternator will operate the engine EEC when (3.D.c)
A. 12%-15% N2 speed is obtained.
B. 52%-55% N2 speed is obtained.
C. 0%-12% N2 speed is obtained.
D. 16%-25% N2 speed is obtained.
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Test 4

 

12. The dispatch levels for the CDU messages are to advise of the fault time limits if necessary, they maybe (3.D.c.)
A. No dispatch, short time or 150 hours, long time 500 hours
B. No dispatch, economic level, ALTN level
C. No dispatch, short time or 250 hours, long time 5,000 hours
D. Both A and B
13. The N1 speed sensor provides signal information from the 30 ring teeth and is used
A. for AVM system to balance the engine and for N2 speed indication
B. for DEU system to balance the engine and for N1 speed indication
C. for AVM system, N1 speed indication for thrust management
D. for DEU system to balance the engine and for N2 speed indication
(3.D.c.)
14. Which indicator in the flight compartment shows the ENG FAIL message? (1.A.a.)
A. The EGT indicator
B. The N1 indicator
C. The N2 indicator
D. The fuel flow indicator
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July 2004
Test 4

15. The CDP sensor or the PS3 line, supplies an air input to the EEC which changes the signal to an electrical signal by (3.C.c.)
A. 4 quartztransducers inside the DEU.
B. 2 quartztransducers inside the CDS.
C.2 quartz transducersinside the ADIRU.
D.2 quartztransducers inside the EEC.
16. The EEC interfaces with the ignition system to control the ignition ______ to the exciter boxes. (3.D.c.)
A. 115 Volts DC
B. 115 Volts AC
C. 400 Volts AC
D. 400 Volts DC
17. There are ______ EHSV's in the HMU that control servo systems. (3.D.c.)
A. two
B. four
C. six
D. eight
18. The HPSOV stops metered fuel flow and is controlled by (3.C.c.)
A. Fire switches
B. Start levers
C. Both A & B
D. Throttle position
19. The starter air valve operates the starter of the engine, with the correct air pressure a manual start is done by (3.D.a.)
A. inserting a 1/4" drive extention through the right thrust reverser cowl and is turned manually to open and close the valve.
B. inserting a 3/8" drive extention through the left fan cowl and is turned manually to open and close the valve.
C. inserting a 1/4" drive extention through the left thrust reverser cowl and is turned manually to open and close the valve.
D. inserting a 3/8" drive extention through the right fan cowl and is turned manually to open and close the valve.
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July 2004
Test 4

20. The compressor airflow control system adjusts the airflow conditions of the high and low compressors to: (3.D.c.)
A. allow the engine to stall and give air to the aircraft bleed systems.
B. controls the clearances of the engine.
C. prevent the engine from stalling for all power conditions.
D. by the VSV's, VBV's and BSV systems.
21. The HPTACC valve controls the ___ and ___ stage airflows to the HPT shroud assembly, which changes the gap between the shroud and
HPT rotor blades. (3.D.c.)
A. 4th and 8th
B. 5th and 9th
C. 4th and 5th
D. 4th and 9th
22. The VBV system uses ______ to open and close the VBV doors: (3.D.c.)
A. a fuel gear motor
B. 2 actuators
C. 2 gear motors
D. 1 actuator
23. The function PT25 sensor is to provide: (3.D.c.)
A. high pressure compressor inlet temperature to the EEC for fuel metering logic
B. low pressure compressor inlet temperature to the EEC for fuel metering logic
C. high pressure compressor inlet pressure to the EEC for fuel metering logic
D. low pressure compressor inlet pressure to the EEC for fuel metering logic
24. The T5 sensor measures the temperature at the outlet of the Low Pressure Turbine and is an optional sensor. (3.C.c)
A. True
B. False
25. The function of the actuator test, on the CDU is to test the; (3.D.c.)
A. VSV and VBV systems only.
B. HPTACC, LPTACC actuators .
C. all valves and actuators, except the FMV.
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D. serves no purpose at all.
July 2004
Test 4