CFM56-7B Advanced Engine Systems Test 4
<P>CFM56-7B Advanced Engine Systems Test 4</P><P>**** Hidden Message *****</P> <P>cfm <BR>The Power <BR>Of Flightcfm <BR>The Power <BR>Of Flight <BR>Name: <BR>Date:</P>
<P> Class Number:</P>
<P> Correct Answers: </P>
<P>Directions: For each of the following questions, circle the letter that is the most correct answer. </P>
<P>1. Inside the fuel assembly there are ____ pump(s) and _____ shaft(s). (3.D.c) <BR>A. __3__ pumps and ___2__ shafts <BR>B. __1__ pumps and ___1__ shafts <BR>C. __2__ pumps and ___2__ shafts <BR>D. __2__ pumps and ___3__ shafts <BR>2. The IDG fuel to oil cooler or heat exchanger, is in series with the ___________ to cool the IDG oil. (3.D.c) <BR>A. IDG servo fuel heater found in ATA chapter 72-00-00, <BR>B. IDG air/fuel cooler found in ATA chapter 71-00-00, <BR>C. IDG fuel/oil cooler found in ATA chapter 73-00-00, <BR>D. IDG air/oil cooler found in ATA chapter 24-00-00, <BR>3. The EEC controls the Burner staging valve by: (3.D.c) <BR>A. an EHSV in the HMU sending an electrical signal to open or close the BSV. <BR>B. an EHSV in the HMU sending an servo signal to open or close the BSV. <BR>C. a solenoid in the HMU sending a servo signal to open or close the BSV. <BR>D. a solenoid in the HMU sending an electrical signal to open or close the BSV. <BR>4. The operation of the servo fuel heater is to. (2.C.b) <BR>A. To prevent hot oil temperatures in the IDG cooling system. <BR>B. To help cool the engine fuel into the fuel nozzles. <BR>C. To direct oil, fuel, hydraulic fluid, water and vapor overboard. <BR>D. To prevent ice in the servo systems. <BR>5. The fuel nozzle shrouds on the fuel manifold___ (3.D.c) <BR>A. To prevent oil contact with hot engine areas by enclosing and sealing of the fuel nozzle B-nut connection . <BR>B. To prevent fuel contact with hot engine areas by enclosing and sealing of the fuel nozzle B-nut connection . <BR>C. allows a leaking fuel nozzle B-nut connection to drain overboard through a drain line. <BR>Page 1 <BR>D. To prevent fuel contact with fan areas of the fuel nozzle B-nut connection . <BR>July 2004 <BR>Test 4 <BR><BR>CFM56-7B Advanced Engine Systems Test 4 </P>
<P>6. The EEC switches for the CFM56-7 engine will display a amber ALTN in the flight compartment when. (3.D.c) <BR>A. Pressure total is no loner valid from both ADIRU's. <BR>B. the PT25 sensor is no loner valid from both ADIRU's. <BR>C. the PT25 sensor is no loner valid. <BR>D. Pressure total is no loner valid from either of the ADIRU's. <BR>7. The ENGINE CONTROL light is to alert the flight crew that (3.D.c) <BR>A. a flame out has happened in flight <BR>B. the engine has failed <BR>C. a no dispatch condition alert on the ground for the flight crew <BR>D. a no dispatch condition alert on the ground and in flight, for the flight crew <BR>8. How is the engine serial number changed in the CDU for CFM56-7 engine if another one is installed? (3.D.c) <BR>A. You change the metal engine data plate near the oil tank. <BR>B. The serial number is read directly from the ID plug. <BR>C. It can not be changed except by the FAA. <BR>D. The technician is required to change it through the CDU. <BR>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) <BR>A. not used once the aircraft is in flight <BR>B. invalid till the aircraft is in flight. <BR>C. inhibited above 15,500 feet and or Mach number is above .45. <BR>D. not inhibited above 15,500 feet and or Mach number is above .45. <BR>10. The EEC alternator will operate the engine EEC when (3.D.c) <BR>A. 12%-15% N2 speed is obtained. <BR>B. 52%-55% N2 speed is obtained. <BR>C. 0%-12% N2 speed is obtained. <BR>D. 16%-25% N2 speed is obtained. <BR>Page 2 <BR>July 2004 <BR>Test 4 </P>
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<P>12. The dispatch levels for the CDU messages are to advise of the fault time limits if necessary, they maybe (3.D.c.) <BR>A. No dispatch, short time or 150 hours, long time 500 hours <BR>B. No dispatch, economic level, ALTN level <BR>C. No dispatch, short time or 250 hours, long time 5,000 hours <BR>D. Both A and B <BR>13. The N1 speed sensor provides signal information from the 30 ring teeth and is used <BR>A. for AVM system to balance the engine and for N2 speed indication <BR>B. for DEU system to balance the engine and for N1 speed indication <BR>C. for AVM system, N1 speed indication for thrust management <BR>D. for DEU system to balance the engine and for N2 speed indication <BR>(3.D.c.) <BR>14. Which indicator in the flight compartment shows the ENG FAIL message? (1.A.a.) <BR>A. The EGT indicator <BR>B. The N1 indicator <BR>C. The N2 indicator <BR>D. The fuel flow indicator <BR>Page 3 <BR>July 2004 <BR>Test 4 </P>
<P><BR>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.) <BR>A. 4 quartztransducers inside the DEU. <BR>B. 2 quartztransducers inside the CDS. <BR>C.2 quartz transducersinside the ADIRU. <BR>D.2 quartztransducers inside the EEC. <BR>16. The EEC interfaces with the ignition system to control the ignition ______ to the exciter boxes. (3.D.c.) <BR>A. 115 Volts DC <BR>B. 115 Volts AC <BR>C. 400 Volts AC <BR>D. 400 Volts DC <BR>17. There are ______ EHSV's in the HMU that control servo systems. (3.D.c.) <BR>A. two <BR>B. four <BR>C. six <BR>D. eight <BR>18. The HPSOV stops metered fuel flow and is controlled by (3.C.c.) <BR>A. Fire switches <BR>B. Start levers <BR>C. Both A & B <BR>D. Throttle position <BR>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.) <BR>A. inserting a 1/4" drive extention through the right thrust reverser cowl and is turned manually to open and close the valve. <BR>B. inserting a 3/8" drive extention through the left fan cowl and is turned manually to open and close the valve. <BR>C. inserting a 1/4" drive extention through the left thrust reverser cowl and is turned manually to open and close the valve. <BR>D. inserting a 3/8" drive extention through the right fan cowl and is turned manually to open and close the valve. <BR>Page 4 <BR>July 2004 <BR>Test 4 </P>
<P><BR><BR>20. The compressor airflow control system adjusts the airflow conditions of the high and low compressors to: (3.D.c.) <BR>A. allow the engine to stall and give air to the aircraft bleed systems. <BR>B. controls the clearances of the engine. <BR>C. prevent the engine from stalling for all power conditions. <BR>D. by the VSV's, VBV's and BSV systems. <BR>21. The HPTACC valve controls the ___ and ___ stage airflows to the HPT shroud assembly, which changes the gap between the shroud and <BR>HPT rotor blades. (3.D.c.) <BR>A. 4th and 8th <BR>B. 5th and 9th <BR>C. 4th and 5th <BR>D. 4th and 9th <BR>22. The VBV system uses ______ to open and close the VBV doors: (3.D.c.) <BR>A. a fuel gear motor <BR>B. 2 actuators <BR>C. 2 gear motors <BR>D. 1 actuator <BR>23. The function PT25 sensor is to provide: (3.D.c.) <BR>A. high pressure compressor inlet temperature to the EEC for fuel metering logic <BR>B. low pressure compressor inlet temperature to the EEC for fuel metering logic <BR>C. high pressure compressor inlet pressure to the EEC for fuel metering logic <BR>D. low pressure compressor inlet pressure to the EEC for fuel metering logic <BR>24. The T5 sensor measures the temperature at the outlet of the Low Pressure Turbine and is an optional sensor. (3.C.c) <BR>A. True <BR>B. False <BR>25. The function of the actuator test, on the CDU is to test the; (3.D.c.) <BR>A. VSV and VBV systems only. <BR>B. HPTACC, LPTACC actuators . <BR>C. all valves and actuators, except the FMV. <BR>Page 5</P>
<P>D. serves no purpose at all. <BR>July 2004 <BR>Test 4 </P> 感谢楼主的分享 感谢楼主的分享 好东西，学习学习
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