FAA AMT POWERPLANT QUESTIONS

A COOL-OFF PERIOD PRIOR TO SHUTDOWN OF A TURBINE ENGINE IS ACCOMPLISHED IN ORDER TO: allow the turbine wheel to cool before the case contracts around it. prevent seizure of the engine bearings. prevent vapor lock in the fuel control and/or fuel lines.

THE PRIMARY CONCERN IN ESTABLISHING THE FIRING ORDER FOR AN OPPOSED ENGINE IS TO: provide for balance and eliminate vibration to the greatest extent possible. keep the power impulses on adjacent cylinders as close as possible in order to obtain the greatest mechanical efficiency. keep power impulses on adjacent cylinders as far apart as possible in order to obtain the greatest mechanical efficiency.

HOW ARE THE TEETH OF THE GEARS IN THE ACESSORY SECTION OF AN ENGINE NORMALLY LUBRICATED?. by submerging the load bearing portions in oil. by splashed or sprayed oil. by surrounding the load bearing portions with baffles or housings within which oil pressure can be maintained.

MOTOR DRIVEN IMPELLER AND TURBINEFUEL FLOW TRANSMITTERS ARE DESIGNATED TO TRANSMIT DATA: mechanically. by fuel pressure. using aircraft electrical system power.

WHICH OF THE FOLLOWING ENGINE SERVICING OPERATING GENERALLY REQUIRES ENGINE PRE OILING PRIOR TO STARTING THE ENGINE?. replacement of oil lines. engine oil and filter change. engine installation.

THE VELOCITY OF SUBSONIC AIR AS IT FLOWS THROUGH A CONVERGENT NOZZLE: decreases. increases. remains constant.

IF AN AIRCRAFT IGNITION SWITCH IS TURNED OFF AND THE ENGINE CONTINUES TO RUN NORMALLY, THE TROUBLE IS PROBABLY CAUSED BY: arcing magneto breaker points. an open ground lead in the magneto. primary lead grounding.

WHAT IS THE PRINCIPAL ADVANTAGE OF USING PROPELLER REDUCTION GEARS?. to enable the engine RPM to be increased with an accompanying increase in power and allow the propeller to remain at a lower, more efficient RPM. to enable the propeller RPM to be increased without an accompanying increase in engine RPM. to enable the engine RPM to be increased with an accompanying increase in propeller RPM.

SHIELDING IS USED ON SPARK PLUG AND IGNITION WIRES TO: prevent outside electromagnetic emissions from disrupting the operation of the ignition system. prevent interference with radio reception. protect the wires from short circuits as a result of chafing or rubbing.

WHAT EFFECT DOES HIGH ATMOSPHERIC HUMIDITY HAVE ON THE OPERATION OF A JET ENGINE?. has a little or no effect. decreases engine pressure ratio. decreases compressor and turbine RPM.

WHAT ARE THE POSITIONS OF THE PRESSURIZATION VALVE AND THE DUMP VALVE IN A JET ENGINE FUEL SYSTEM WHEN THE ENGINE IS SHUT DOWN?. pressurization valve open, dump valve open. pressurization valve closed, dump valve open. pressurization valve closed, dump valve closed.

WHERE PHYSICAL SEPARATION OF THE FUEL LINES FROM ELECTRICAL WIRING OR CONDUIT IS IMPRACTICABLE, LOCATE THE FUEL LINE: above the wiring and clamp the line securely to the airframe structure. inboard of the wiring and clamp both securely to the airframe structure. below the wiring and clamp the line securely to the airframe structure.

IF THE IGNITION SWITCH IS MOVED FROM "BOTH" TO EITHER "LEFT" OR "RIGHT" DURING AN ENGINE GROUND CHECK, NORMAL OPERATION IS USUALLY INDICATED BY A: slight drop in RPM. momentary interruption of both ignition systems. a large drop in RPM.

IF AN ENGINE IS EQUIPPED WITH A FLOAT TYPE CARBURETOR AND THE ENGINE RUNS EXCESSIVELY RICH AT FULL THROTTLE, A POSSIBLE CAUSE OF THE TROUBLE IS A CLOGGED: atmospheric vent line. back suction line. main air bleed.

IF AN ENGINE CYLINDER IS TO BE REMOVED, AT WHAT POSITION IN THE CYLINDER SHOULD THE PISTON BE?. top dead center. bottom dead center. halfway between top and bottom dead center.

AN INDICATION OF UNREGULATED POWER CHANGES THAT RESULT IN CONTINUAL DRIFT OF MANIFOLD PRESSURE INDICATION ON A TURBOSUPER-CHARGED AIRCRAFT ENGINE IS KNOWN AS: waste gate fluctuation. bootstrapping. overshoot.

THE DENSITY OF AIR IS VERY IMPORTANT WHEN MIXING FUEL AND AIR TO OBTAIN A CORRECT FUEL TO AIR RATIO WHICH OF THE FOLLOWING WEIGHS THE MOST?. 100 parts of dry air. 50 parts of dry air and 50 parts of water vapor. 75 parts of dry air and 25 parts of water vapor.

SODIUM FILLED VALVES ARE ADVANTAGEOUS TO AN AVIATION ENGINE BECAUSE THEY: dampen valve impact shocks. dissipate heat well. are lighter.

WHAT PRECAUTION SHOULD BE TAKEN WHEN PUTTING THREAD LUBRICANT ON A TAPERED PIPE PLUG IN A CARBURETOR FLOAT BOWL?. do not use thread lubricant on any carburetor fitting. put the thread lubricant only on the first thread. engage the first thread of the plug, then put a small amount of lubricant on the second thread and screw the plug in.

THE PROPELLER GOVERNOR CONTROLS THE: spring tension on the boost pump speeder spring. oil to and from the pitch changing mechanism. linkage and counterweights from moving in and out.

THE PRIMARY CONDITION(S) THAT ALLOW(S) MICROORGANISMS TO GROW IN THE FUEL IN AIRCRAFT FUEL TANKS IS (ARE): the presence of water. the presence of dirt or other particulate contaminants. warm temperatures and frequent fueling.

WHICH OF THE FOLLOWING IS IDENTIFIED AS THE CAMBERED OR CURVED SIDE OF A PROPELLER BLADE, CORRESPONDING TO THE UPPER SURFACE OF A WING AIRFOIL SECTION: blade back. blade chord. blade face.

HOW ARE MOST AIRCRAFTS TURBINE ENGINES FIRE EXTINGUISHING SYSTEMS ACTIVATED?. electrically discharged cartridges. pushrod assembly. manual remote control valve.

WHAT WILL RESULT IF AN OIL FILTER BECOMES COMPLETELY BLOCKED?. oil will flow at the normal rate through the system. oil will flow at a reduced rate through the system. oil flow to the engine will stop.

WHAT IS THE SMALLEST TERMINAL STUD ALLOWED FOR AIRCRAFT ELECTRICAL POWER SYSTEMS?. no. 10. no. 6. no. 8.

WHEN AIRCRAFT TURBINE BLADES ARE SUBJECTED TO EXCESSIVE HEAT STRESS, WHAT TYPE OF FAILURES WOULD YOU EXPECT?. torsion and tension. stress rupture. bending and torsion.

AIRCRAFT ELECTRICAL WIRE SIZE IS MEASURED ACCORDING TO THE: technical standard order system. military specification system. american wire gauge system.

AFTER A FIRE IS EXTINGUISHED, OR OVERHEAT CONDITION REMOVEDIN AIRCRAFT EQUIPPED WITH A "SYSTRON-DONNER" FIRE DETECTOR, THE DETECTION SYSTEM: must be manually reset. sensing component must be replaced. automatically resets.

(REFER TO POWERPLANT FIG. 7). WHAT IS THE PURPOSE OF THE FUEL TRANSFER EJECTORS?. to supply fuel under pressure to the engine driven pump. to assist in the transfer of fuel from the main tank to the boost pump sump. to transfer fuel from the boost pump sump to the wing tank.

THE BLENDING OF BLADES AND VANES IN A TURBINE ENGINE: may sometimes be accomplished with the engine installed, ordinarily using power tools. should be performed parallel to the length of the blade using smooth contours to minimize stress points. is usually accomplished only at engine overhaul.

SELECT A CHARACTERISTIC OF A GOOD WELD ON EXHAUST STACKS: porousness or projecting globules should show in the weld. the weld should be built up 1/8 inch. the weld should taper off smoothly into the base metal.

AN AIRCRAFT CARBURETOR IS EQUIPPED WITH A MIXTURE CONTROL IN ORDER TO PREVENT THE MIXTURE FROM BECOMING TOO: rich at high altitudes. lean at high altitudes. rich at high speeds.

INCREASED WATER VAPOR (HIGHER RELATIVE HUMIDITY) IN THE INCOMING AIR TO A RECIPROCATING ENGINE WILL NORMALLY RESULT IN WHICH OF THE FOLLOWING?. a leaning effect on engines which use non automatic carburetors. decreased engine power at a constant RPM and manifold pressure. increased power output due to increased volumetric efficiency.

SOME AIRCRAFT ENGINE MANUFACTURERS EQUIP THEIR PRODUCT WITH CHOKED OR TAPER-GROUND CYLINDERS IN ORDER TO: provide a straight cylinder bore at operating temperatures. flex the rings slightly during operation and reduce the possibility of the rings sticking in the grooves. increase the compression pressure for starting purposes.

DURING GROUND OPERATIONS OF AN ENGINE, THE COWL FLAPS SHOULD BE IN WHAT POSITION?. fully closed. opened according to ambient conditions. fully open.

THE HORSEPOWER DEVELOPED IN THE CYLINDERS OF A RECIPROCATING ENGINE IS KNOWN AS THE: shaft horsepower. indicated horsepower. brake horsepower.

IF THE OIL PRESSURE GAUGE FLUCTUATORS OVER A WIDE RANGE FROM ZERO TO NORMAL OPERATING PRESSURE, THE MOST LIKELY CAUSE IS: air lock in the scavenge pump intake. broken or weak pressure relief valve spring. low oil supply.

SOME BARREL CYLINDER ARE HARDENED BY: nitriding. shot peening. tempering.

WHICH OF THE FOLLOWING IS THE ULTIMATE LIMITING FACTOR OF TURBINE ENGINE OPERATION?. compressor inlet air temperature. turbine inlet temperature. burner can pressure.

(REFER TO POWERPLANT FIGURE 6.) WHICH CURVE MOST NEARLY REPRESENTS AN AIRCRAFT ENGINE`S FUEL/AIR RATIO THROUGHOUT ITS OPERATING RANGE?. 2. 3. 1.