CFM

1- For a borescope inspection on the high pressure turbine blades... you turn the fan rotor. you turn the rotor via the starter drive pad on the accessory gearbox. you turn the rotor via the hand crank pad on the accessory gearbox.

2- The Spinner rear cone is made of: Titanium. Composite. Aluminum alloy.

3- The High Pressure Turbine Clearance Control valve applies... ...4th and (or) 9th stage high pressure compressor bleed air to the high pressure turbine case. ... 9th stage high pressure compressor bleed air to the high pressure turbine disk. ...4th and (or) 9th stage high pressure compressor bleed air to the high pressure turbine rotor.

4- Structural Strenght for the Fan Frame is obtained from: FWD sump. 12 Struts. TRF.

5- The main purpose of the EIU is: to acquire all engine data and parameters and send them to the ECAM system. to separate and isolate the engine from the other aircraft systems and computers, transfering certain data/parameters. to send the different commands and signals from the ECU to the engine.

6- The Low oil pressure condition is activated at: 25 PSI increasing pressure. 13 PSI decreasing pressure. 90 PSI.

7- ENHANCED. Where are the lavatory smoke detectors connected?. SDF (Smoke Detection Function) in the CIDS Directors. SDCU (Smoke Detection Control Unit). SDF (Smoke Detection Function) in the CIDS Directors through DEU - B (Decoder Encoder Unit).

8- The LPC and LPT are fixed to: An outer shaft called N1. An inner shaft called N2. An inner shaft called N1.

9- The combustion case encloses: 18 fuel nozzles, 2 igniters and 4 borescope ports. 20 fuel nozzles, 2 igniters and 2 borescope ports. 20 fuel nozzles, 2 igniters and 6 borescope ports.

10- The APU provides for automatic fire extinguishing: On the ground and in flight. Only when selected to automatic by ground personnel. On the ground only.

11- The AFT Engine Mount carries....... weight, rotation, side and vertical load. thrust,weight, rotation, side and vertical load. weight, axial, vertical and rotation load.

12- Which warning lights are triggered in case of an avionic smoke detection?. GEN 1 LINE SMOKE and BLOWER and EXTRACT FAULT lights. GEN 1 LINE SMOKE light. BLOWER FAULT.

13- What condition(s) must be given to activate the ignition system. The mode selector in NORM and the Master Sw in ON. The Mode selector in Ignition/Start and Master Sw. in ON. The Mode Selector in Crank or Ignition/Start and Master Sw. in ON.

14- (CFM56-5B) In case of total alternator failure, the ECU will receive: 28 VDC as a back up from A/C network. 28 VDC as a back up from the other engine. 115 VAC as a back up from A/C network.

15- The Variable Bleed Valve System... ...is operated by a fuel gear pump. ...is operated by one fuel gear motor. ...is operated by two linear fuel hydraulic actuators.

16- (CFM56-5B) Where are the fan balancing screws installed?. On the spinner rear cone. On the spinner front cone. On the fan disk.

17- The Bearing # 3 is to: HP Shaft. N1, foward part. LP Shaft.

18- The Smoke in the Avionics compartment is detected by ... AEVC. FWC. Avionics smoke detector.

19- The location of the N2 speed sensor is: AGB rear face. AGB front face. Transfer Gear Box.

20- The FADEC system consist of: ECU, EIU and HMU. ECU, HMU and Peripheral components. ECU, EIU and EVMU.

21- What is the reason for the ECAM Message ENG1 FIRE LOOP A FAULT?. Loop A and B of Engine1 detected a fire. Loop A of Engine1 detected a fault of electrical failure. Loop A and B of Engine1 detected a fault within less than five seconds.

22- On the ECAM page, the main parameters of the engines are: N1-N2-EGT-F.F.-VIB. N1-N2-EGT-F.F. N1-N2-EGT.

23- In relation to Engine Mounts, the engine thrust is transferred to the pylon through: both, the fwd and aft mounts. the aft mount. the fwd mount.

24- The engine anti ice valve is: electrically controlled, spring force operated. electrically operated and controlled. electrically controlled, pneumatically operated.