EXAMEN ATA 70 CFM 56

IN NORMAL CONDITIONS, THE OIL SYSTEM INDICATIONS SHOW. Quantity, temperature and pressure indications. Quantity, temperature and clogging filter indications.

THE PURPOSE OF THE FUEL RETURN VALVE (FRV) IN THE CIRCULATION SYSTEM IS: To depressurize the fuel system at engine shutdown. To provide better fuel filtering. To maintain Integrated Drive Generator (IDG) oil, engine oil and fuel temperature within limits.

THE FORWARD SUMP IS IN THE FAN FRAME AND IS THE LOCATION OF BEARINGS. No.1, No.2 (fan/booster shaft) and No.3 (High Pressure (HP) shaft forward part). No.4 (HP shaft aft part) and No.5 (Low Pressure (LP) shaft aft part) and No.4 (HP shaft aft part). No.1, No.2 (fan/booster shaft), No.3 (HP shaft forward part).

THE THRUST REVERSER COWL DOORS ARE OPENED. Electrically by a motor or manually and secured by a hold open rod. Hydraulically or manually and secured by two hold open rods. Hydraulically and secured by a hold open rod.

THE LUBRICATION UNIT INCLUDES: Only a single pressure pump. Four scavenge pumps with their respective screens. A single pressure pump and four scavenge pumps with their respective screens.

TURBINE CLEARANCE CONTROL SYSTEMS IS TO: Prevent overheating of the turbine case. Reduce wear of the turbine blades. Optimize engine performance.

NACELLE TEMPERATURE SENSOR MONITORS THE: Accessory gearbox area temperature only. Pylon area temperature only. Core compartment temperature.

THE ELECTRONIC CONTROL UNIT (ECU) IS LOCATED: In the avionics compartment. On the engine turbine rear frame (TRF). On the engine fan case.

THE ENGINE INTERFACE UNIT (EIU): Computes auto-thrust signals. Is required for thrust reverser operation. Controls the engine operation.

DURING MAINTENANCE TASK YOU MUST INSTALL THE HCU PIN TO PROTECT YOU FROM DEATH. WHAT YOU MUST DO?. Be sure the pin has a red flag and write down a report in the maintenance log. Be sure the pin has a red flag and you must advise at inspection personnel. Be sure the pin has a red flag and your supervisor must be advised about it.

TO REPLACE THE FIRE EXTINGUISHER BOTTLE YOU MUST. Remove the electrical connector and install immediately the dummy protector. Remove the bottle and install again but in reverse order. Remove the hoses and electrical connector, then remove the bolts that secure the bottle.

WHICH AREAS IN THE ENGINE ARE MONITORED BY FIRE: Fan case, core and pylon areas. Fan case and core areas. Core, exhaust and fan case areas.

IN REFERENCE WITH THE FIRE EXTINGUISHING BOTTLES: All bottles can be discharged even if the aircraft is de-energized. Only the engine bottles number 1 and APU are connected to the hot battery bus. The left bottles can be used if the right engine catches fire.

TO OBTAIN AN ENGINE FIRE WARNING IN THE COCKPIT, THE LOOPS A AND B MUST HAVE: Fire on loop A and loop B. Fire on loop A and fault on loop B or vice versa. Damage of two loops at the same time. All three answers A, B and C are correct.

WHICH AREA IN THE LAVATORY IS AUTOMATIC PROTECTED AGAINST FIRE?. Lavatory passenger areas. All electrical circuits in the lavatory. Lavatory waste bin.

THE NUMBER OF DISCHARGE HEADS PER EXTINGUISHER BOTTLE FOR CARGO COMPARTMENTS IS/ARE. Only one, dedicated for the FWD cargo compartment. One dedicated for the FWD cargo compartment and one dedicated for the AFT/BULK cargo compartment. Two, dedicated for the FWD and two for the AFT/BULK cargo compartment.

THE CARGO COMPARTMENTS ARE PROTECTED AGAINST FIRE WITH: Smoke detection. Smoke detection and operable fire extinguisher bottle. Fire detection and operable extinguishing system.

TO ACCOMPLISH THE AUTO-EXTINGUISHING TEST OF THE APU: The APU must be running and master sw ON. The APU must be shutdown, master sw ON, auto-extinguished test on 50 VU. The APU must be shutdown and Master SW selected ON, and start PB ON.

THE CARGO COMPARTMENTS SMOKE DETECTORS ARE MONITORED BY (ENHANCED AIRCRAFT): AEVC. CIDS-SDF. SDCU.

IN REFERENCE WITH THE ENGINE FIRE P/B INTERFACES: FADEC system will be de-energized if Fire P/B is released out. FADEC system will still be energized regardless of Fire P/B position. Fire P/B doesn't affect the electrical supply to the FADEC system.

THE COMPONENTS OF THE COMBUSTION SECTION ARE: The igniter plug, ten fuel nozzles and one direct annular combustion chamber. Two igniter plugs, nine fuel nozzles, one reverse annular combustion chamber. The Inlet Guide Vane assembly, two igniter plugs, two fuel nozzles and one annular combustion chamber.

THE APU START EVENTS SEQUENCE IS INITIATED BY: The APU Master Switch pushbutton. The APU BATT pushbutton. The APU START pushbutton.

WHEN THE APU MASTER SWITCH IS SET TO 'ON', THE APU FUEL PUMP RUNS: Continuously. As long as the main engine fuel feed line pressure is lower than certain value. Only if the Electronic Control Box detects an HP pump failure.

A MANUAL OVERRIDE DEVICE USED BY MEL, IS PROVIDED FOR: The air intake flap. The relay box. The Inlet Guide Vane.

THE DESIGN TYPE OF THE LOAD SECTION COMPRESSOR IS: Two-stage centrifugal compressor design. Single stage centrifugal compressor. Three-stage axial compressor design.

WHICH ELEMENT CUT OFF OR PROVIDE FUEL TO THE FLOW DIVIDER AND NOZZLES?. three-way solenoid valve. Fuel metering valve. Pressure and regulating valve.

WHAT HAPPENED IF LOW OIL PRESSURE IS REACHED DURING APU OPERATION?. The automatic shutdown of the APU is initiated by ECB. The APU must be shut down as soon as possible. The APU-GEN must be disconnected immediately.

THE LUBRICATION MODULE PROVIDES LUBRICATING OIL TO: The generator, the gearbox and the main shaft bearings. The gearbox only. The generator and the gearbox.

WHICH ELEMENT CONTROLS THE AMOUNT OF AIR THAT GOES INTO LOAD COMPRESSOR?. Load control valve. Surge control valve. Inlet guide vane.

AT 55% THE ECB WILL CUT THE ELECTRICAL SUPPLY TO: The ignition system and bleed air valve. Fuel lo press valve and APU fuel pump. The starter, DE-oil solenoid valve and ignition system.