Systems Atpl PDF

March 27, 2018 | Author: May Be | Category: Jet Engine, Engines, Gas Turbine, Gas Compressor, Turbocharger


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Casa de lucas -"Conditioned" air is air that has: BEEN CONTROLLED IN RESPECT OF TEMPERATURE AN D PRESSURE.-"Frequency wild" in relation to a AC generation system means the generator: OUT PUT FREQUENCY VARIES WITH ENGINE SPEED. -"Nose wheel shimmy" may be described as: A POSSIBLY DAMAGING VIBRATION OF THE N OSE WHEEL WHEN MOVING ON THE GROUND. -"Vapour lock" is the phenomenon by which: HEAT PRODUCES VAPOUR BUBBLES IN THE F UEL LINE. -"Vapour lock" is the phenomenon by which: HEAT PRODUCES VAPOUR BUBBLES IN THE F UEL LINE. -A "fan" stage of a ducted-fan turbine engine is driven by: THE LOW PRESSURE TUR BINE. -A "trip-free" type circuit breaker is a circuit protection device which : WILL NOT ALLOW THE CONTACTS TO BE HELD CLOSED WHILE A CURRENT FAULT EXISTS IN THE CIRCUIT. -A "Zener" diode is used for: VOLTAGE STABILISATION. -A 3 phase AC generator has 3 separate stator windings spaced at: 120°. -A booster or LP compressor in a twin spool turbofan: ROTATES AT THE SAME ROTOR SPEED AS THE FAN. -A bus-bar is: A DISTRIBUTION POINT FOR ELECTRICAL POWER. -A cabin pressure controller maintains a pre-set cabin altitude by regulating th e: POSITION OF THE OUTFLOW VALVE(S). -A cabin rate of descent: RESULTS IN A CABIN PRESSURE INCREASE. -A cantilever wing is: A WING ATTACHED TO THE FUSELAGE AT THE WING ROOT ONLY. -A capacitor in parallel with breaker points: INDUCES A VERY HIGH VOLTAGE ACROSS THE SECONDARY WINDINGS. -A chip detector in the oil system of an engine/gearbox is to indicate that: THE RE ARE METAL PARTICLES IN THE OIL -A composite structural component consists of: A MATRIX AND FIBRES. -A condenser in parallel with breaker points will: INTENSIFY CURRENT IN SECONDAR Y WINDING -A constant speed drive (CSD) that has been disconnected in flight: CAN BE RESET ONLY ON THE GROUND AFTER ENGINE SHUT-DOWN. -A Constant Speed Drive aims at ensuring: THAT THE ELECTRIC GENERATOR PRODUCES A CONSTANT FREQUENCY. -A continuous loop detector system is a: OVERHEAT DETECTION SYSTEM. -A CSD of an AC generator may be disconnected in flight. The primary reason(s) f or disconnection are : LOW OIL PRESSURE AND/OR HIGH OIL TEMPERATURE OF THE GENERATOR DRIVE. -A CSD unit is normally provided with means of monitoring during flight the: OIL TEMPERATURE AND PRESSURE. -A CSD unit which has been disconnected in flight : MAY BE RESET ON THE GROUND O NLY, AFTER ENGINE SHUT-DOWN. -A current limiter fuse in a DC generation system is used to: ALLOW A SHORT TERM OVERLOAD BEFORE RUPTURING. -A diffuser in a gas turbine engine is a device in which the: PRESSURE RISES AND VELOCITY FALLS. -A diluter demand oxygen regulator selected to "100%":DELIVERS OXYGEN FLOW WHEN INHALING. -A FADEC on a gas turbine engine: IS SINGLE FAULT TOLERANT. -A fault protection circuit in a fire detection system will: INHIBIT THE FIRE DE TECTOR WHEN THE DETECTION LINE IS CONNECTED TO GROUND. -A feeder fault on a direct current circuit results from a flux unbalance betwee n the: VOLTAGE COIL AND THE SERIES WINDING TURN. -A flat rated turbofan engine has a constant maximum rated thrust level: UP TO A SPECIFIC OAT. -A flat rated turbofan will be temperature limited if: OAT IS HIGHER THAN FLAT R ATED -A flight control surface actuator is said to be "reversible" when: THERE IS FEE DBACK TO THE PILOT''S CONTROLS OF THE AERODYNAMIC FORCES ACTING ON THE CONTROL SURFACE. -A gaseous sensor/responder tube fire sensor is tested by: HEATING UP THE SENSOR WITH TEST POWER CONNECTION. -A gas turbine engine turbine section may employ active clearance control: TO PR OVIDE ENHANCED CLEARANCES BETWEEN THE BLADE TIPS AND THE CASING. -A gas turbine engine is run at ground idle for a period of time prior to shutdo wn to: PREVENT SEIZURE OF THE ROTOR BLADES IN THEIR SEALS. -A flight control surface actuator is said to be "irreversible" when: THERE IS N O FEEDBACK TO THE PILOT'S CONTROLS OF THE AERODYNAMIC FORCES ACTING ON THE CONTROL SURFACE. -A fuel strainer when fitted to a carburettor will be positioned: UPSTREAM OF TH E NEEDLE VALVE. -A hung (abortive) start of a gas turbine engine may be caused by: A TOO LOW PNE UMATIC STARTER PRESSURE. .TEMPERATURE. -A gas turbine engine turbine section may employ active clearance control: TO PR OVIDE ENHANCED CLEARANCES BETWEEN THE BLADE TIPS AND THE CASING. -A gaseous fire loop system is tested by: HEATING UP THE SENSOR. -A hydraulic shuttle valve: ENABLES AN ALTERNATE SUPPLY TO OPERATE AN ACTUATOR. -A passenger emergency mask is a : A CONTINUOUS FLOW MASK AND CANNOT BE USED IF THERE IS SMOKE IN THE CABIN. -A magnetic circuit-breaker is: A PROTECTION SYSTEM THAT HAS A QUICK TRIPPING RESPONSE. . -A manual inflation handle: SERVES TO ACTUATE INFLATION OF A SLIDE WHEN AUTOMATI C INFLATION FAILS -A mixture setting richer than best power has to be used during climb segments. -A magnetic plug can be used to: COLLECT FERROUS PARTICLES REACHING THE SUMP -A magnetic plug in an engine oil system can be used to: COLLECT FERROUS PARTICL ES. It also supplies both in the air (subject to certification limitations) and on t he ground: AIR CONDITIONING AND ELECTRICAL SERVICES. This results in: LOWER CYLINDER HEAD TEMPERATURE. -A Krueger flap is normally located at the: LEADING EDGE. -A non-cantilever wing is: A WING SUPPORTED BY BRACES OR A STRUT CONNECTED TO TH E FUSELAGE.-A hydraulic low pressure alert is the first indication of: THE PUMP OUTPUT PRES SURE BEING INSUFFICIENT. -A modern Auxiliary Power Unit (APU) is designed to provide power for ground sta rting of an engine. It undergoes a rapid decompressi on so that the pressure in the cabin goes quickly down to the outside pressure value. Which of the following statements is correct about the oxygen system? THE OXYGEN MASKS ARE AUTOMATICALLY PRESENTED TO CABIN CREW MEMBERS AND PASSENGERS -A pressurized aeroplane is operated at FL 300. -A piston engine may use a fuel of a different grade than the recommended: PROVI DED THAT THE GRADE IS HIGHER -A pressure regulator is used in a hydraulic system: IN CONJUNCTION WITH A CONST ANT DELIVERY TYPE PUMP. -A pressure relief valve that does not fit on its seat properly would result in: LOW OIL PRESSURE -A pressurised aeroplane is flying at FL 370 and experiences a rapid decompressi on. -A pilot can actuate the feathering system by: PULLING THE PROPELLER CONTROL LEV ER REARWARDS. -A pilot can determine the amount of oxygen in a bottle by observing its: PRESSU RE.-A passenger oxygen mask is: A CONTINUOUS FLOW MASK AND IN PRINCIPLE SHOULD NOT BE USED IF THERE IS SMOKE IN THE CABIN. What happ ens concerning the oxygen system ? THE OXYGEN MASKS ARE AUTOMATICALLY PRESENTED TO CABIN CREW . -A pressure relief valve in an oil system that does not seat correctly could res ult in: LOW OIL PRESSURE. -A piston engine compression ratio is the ratio of the: TOTAL VOLUME TO THE CLEA RANCE VOLUME. -A safe-life aircraft structural component: MAY BE USED DURING A DECLARED NUMBER OF CYCLES OR FLIGHT HOURS. 3. -A reverse thrust alert on the flight deck occurs when: 1. The combination that regroups all of the correct statements is: 1. -A sandwich structural part is: COMPOSED OF TWO THIN SHEETS AND A LIGHT CORE . -A relay is: A MAGNETICALLY OPERATED SWITCH. the reverser doors are locked with the reverse lever in the stowed position. -A relay is: AN ELECTROMAGNETICALLY OPERATED SWITCH. the reverser doors ar e unlocked with the reverse lever in the stowed position. the reverser doors remain stowed with the reverse lever in t he deployed position. the reverser doors have moved to the reverse thrust position with the reverse lever in the deployed position. -A radio signal looses strength as range from the transmitter increases. 3 -A rich mixture setting has to be used during climb segments. this is called: ATTENUATION -A red or an amber light on an undercarriage position indicator signifies: AT LE AST ONE WHEEL IS IN THE TRAVELLING OR UNLOCKED CONDITION.MEMBERS AND PASSENGERS -A propeller blade is twisted. This results in a: LOWER CYLINDER HEAD TEMPERATURE. -A sandwich structural part is unsuitable for absorbing: CONCENTRATED LOADS. 2. 4. so as to: KEEP THE LOCAL ANGLE OF ATTACK CONSTANT ALONG THE BLADE. -A static converter is powered by: DIRECT CURRENT ON INPUT. THE RETURN MOVEMENT BEING UNDER ANOTHER FORCE. -A single acting actuator: IS POWERED IN ONE DIRECTION ONLY BY HYDRAULIC POWER.MATERIAL. -A semi-monocoque aircraft fuselage structure usually consists of: SKIN. -A smoke hood is a device covering: THE WHOLE HEAD AND WITH A CONTINUOUS OXYGEN FLOW.STRINGERS. -A single action actuator: IS POWERED IN ONE DIRECTION ONLY BY HYDRAULIC POWER. ALTERNATING CURRENT OUTPUT . Its function is to : PREVENT A NY ROTATION OF THE OLEO STRUT IN THE UNDERCARRIAGE SHOCK ABSORBER. -A sandwich type structure is often used in aircraft because of its: LOW MASS AN D HIGH STIFFNESS. THE RETURN MOVEMENT BEING UNDER SPRING FORCE. -A scissor is a component found on landing gears. FRAMES . -A sandwich structural part: CONSISTS OF TWO THIN SHEETS SEPARATED BY A LIGHT CO RE MATERIAL. -A stage in an axial compressor: CONSISTS OF A ROTOR DISC FOLLOWED BY A RING OF STATOR BLADES. -A smoke mask is a: MASK WITH FLOW ON REQUEST AND COVERS THE WHOLE FACE. which does not burst in the event of a tire puncture 6. which requires no rim protection between rim flange and tire removing device 5. 6. which eliminates internal friction between the tube and the tire The combination regrouping all the correct statements is: 1. -A turbo compressor air conditioning system (bootstrap system) will: CAUSE A PRE SSURE DROP AS WELL AS AN ASSOCIATED TEMPERATURE DROP IN THE CHARGE AIR. the primary exchanger (P) and the secondary exchanger (S). whose mounting rim must be flawless 4. -A turbo compressor air conditioning system (bootstrap system) includes two heat exchangers. . -A torsion link assembly is installed on the landing gear to: AVOID ROTATION OF THE PISTON ROD RELATIVE TO THE GEAR OLEO STRUT. which requires solid or branched wheels 2. -A tubeless tyre is a tyre: 1. -A thermal circuit breaker: PROTECTS THE SYSTEM IN THE EVENT OF OVERLOAD/OVERHEATING. The functions of these he at exchangers are as follows: P: PRECOOLS THE ENGINE BLEED AIR S: COOLS AIR BEHIND THE PACK'S COMPRESSOR. 5. -A structure in which the skin takes all of the load is: A MONOCOQUE STRUCTURE. whose valve can be sheared in sudden accelerations 3.-A static inverter is powered by: DIRECT CURRENT AND PRODUCES AN ALTERNATING CURRENT OUTPUT. -A substance which may never be used in the vicinity or on parts of an oxygen in stallation is: GREASE -A test to assess the state of charge of a lead-acid battery would involve: COMP ARING THE "ON-LOAD" AND "OFF-LOAD" BATTERY VOLTAGES. -A turbocharger system in a reciprocating engine is normally driven by: THE EXHA UST SYSTEM. -A turbofan engine with a bypass air mass flow of 200 kg/s and a HP compressor m ass flow of 20 kg/s has a bypass ratio of: 10 -A turbofan engine with a bypass mass flow of 250 kg/s and a HP compressor mass flow of 50 kg/s has a bypass ratio of: 5 -A turbofan engine with a bypass mass flow of 888 kg/s and a HP compressor mass flow of 111 kg/s has a bypass ratio of: 8 -A turbofan engine with an inlet air mass flow of 1000 kg/s and a bypass mass fl ow of 889 kg/s has a bypass ratio of: 8.-A turbocharger in a reciprocating engine consists of a: COMPRESSOR AND TURBINE MOUNTED ON A COMMON SHAFT.01 -A turbofan engine with an inlet air mass flow of 200 kg/s and a HP compressor m ass flow of 20 kg/s has a bypass ratio of: 9 -A turbofan engine with an inlet air mass flow of 220 kg/s and a bypass mass flo w of 200 kg/s has a bypass ratio of: 10 -A turbofan engine with an inlet air mass flow of 220 kg/s and a HP compressor m ass flow of 20 kg/s has a bypass ratio of: 10 .01 -A turbofan engine with an inlet air mass flow of 1000 kg/s and a HP compressor mass flow of 111 kg/s has a bypass ratio of: 8. . 3000 m) -Awing spar typically consists of: A WEB AND GIRDERS. -A twin-spool engine with a bypass mass flow of 250 kg/s and a HP compressor mas s flow of 250 kg/s has a bypass ratio of: 1 -A twin-spool engine with an inlet air mass flow of 220 kg/s and a HP compressor mass flow of 220 kg/s has a bypass ratio of: 0 -A twin-spool engine with an inlet air mass flow of 500 kg/s and a HP compressor mass flow of 250 kg/s has a bypass ratio of: 1 -A twin-spool engine with an inlet air mass flow of 500 kg/s and a bypass mass f low of 250 kg/s has a bypass ratio (BPR) of: 1 -A unit that converts electrical DC into AC is: AN INVERTER.-A turbofan engine with an inlet air mass flow of 300 kg/s and a bypass mass flo w of 250 kg/s has a bypass ratio of: 5 -A turbofan engine with an inlet air mass flow of 300 kg/s and a HP compressor m ass flow of 50 kg/s has a bypass ratio of: 5 -A twin spool gas turbine engine is one in which the: LP TURBINE DRIVES THE LP C OMPRESSOR AND THE HP TURBINE DRIVES THE HP COMPRESSOR. -A warning device alerts the crew in case of an excessive cabin altitude. This w arning must be triggered on reaching the following altitude: 10000 ft (approx. (extremely remote) -According JAR/CS 25 the allowable quantitative average failure probability per flight hour for a catastrophic failure should be on the order of (^ means to the power of): less t han 10^ -9. -According JAR/CS 25 the allowable average failure probability per flight hour f or a minor failure should be on the order of (^ means to the power of): between 10^ -3 and 10^ -5. . -According JAR/CS 25 the worst effect of a catastrophic failure on the occupants of an aeroplane excluding flight crew could be: MULTIPLE FATALITIES. (probable) -According JAR/CS 25 the allowable average failure probability per flight hour p robability for a major failure should be on the order of (^ means to the power of): between 10^ -5 and 10^ -7. -AC generators operated in parallel must have the same: VOLTAGE AND PHASE. -According JAR/CS 25 the worst effect of a hazardous failure on the aeroplane co uld be: LARGE REDUCTION IN FUNCTIONAL CAPABILITIES OR SAFETY MARGINS.-About a twin spool compressor: THE LOW PRESSURE SPOOL RUNS AT A LOWER RPM THAN THE HIGH PRESSURE SPOOL. (extremely improbable) -According JAR/CS 25 the worst effect of a catastrophic failure on the aeroplane could be: HULL LOSS. -According JAR/CS 25 the worst effect of a catastrophic failure on the flight cr ew could be: FATALITIES OR INCAPACITATION. (remote) -According JAR/CS 25 the allowable quantitative average failure probability per flight hour for a hazardous failure should be on the order of (^ means to the power of): between 1 0^ -7 and 10^ -9. the air starter: IS DISENGAGED BY THE COUPLING BETWEEN ENGINE N2 SPOOL AND STARTER BY THE USE OF CENTRIFUGAL FORCES. -According JAR/CS 25 the worst effect of a hazardous failure on the occupants of an aeroplane excluding flight crew could be: SERIOUS OR FATAL INJURY TO A SMALL NUMBER OF PASSENGERS OR CABIN CREW. -According JAR/CS 25 the worst effect of a minor failure on the aeroplane could be: SLIGHT REDUCTION IN FUNCTIONAL CAPABILITIES OR SAFETY MARGINS.-According JAR/CS 25 the worst effect of a hazardous failure on the flight crew could be: PHYSICAL DISTRESS OR EXCESSIVE WORKLOAD. -After a successful start of a high bypass turbofan engine. -According JAR/CS 25 the worst effect of a minor failure on the flight crew coul d be: A SLIGHT INCREASE IN WORKLOAD. IMPAIRS ABILITY TO PERFORM TASKS. -According JAR/CS 25 the worst effect of a major failure on the aeroplane could be: SIGNIFICANT REDUCTION IN FUNCTIONAL CAPABILITIES OR SAFETY MARGINS. -According JAR/CS 25 the worst effect of a major failure on the occupants of an aeroplane excluding flight crew could be: PHYSICAL DISTRESS. -According JAR/CS 25 the worst effect of a major failure on the flight crew coul d be: PHYSICAL DISCOMFORT OR A SIGNIFICANT INCREASE IN WORKLOAD. -According JAR/CS 25 the worst effect of a minor failure on the occupants of an aeroplane excluding flight crew could be: PHYSICAL DISCOMFORT. POSSIBLY INCLUDING INJURIES. . -An AC generator driven by a CSD unit: REQUIRES A VOLTAGE CONTROLLER TO MAINTAIN CONSTANT VOLTAGE UNDER LOAD. -Aircraft fuel tanks should be checked for water: BEFORE THE FIRST FLIGHT OF THE DAY.-After air has passed through the compressor of a gas turbine engine the: TEMPER ATURE WILL BE HIGHER THAN THE INLET TEMPERATURE. shear stress es The combination regrouping all the correct statements is : 1. -Among the different types of aircraft structures. . the shell structures efficien tly transmit the: 1. -An aeroplane equipped with irreversible flight controls: REQUIRES AN ARTIFICIAL FEEL SYSTEM. tangent bending stresses 3. 3 -An abortive (hung) start is the term used to describe an attempt to start in wh ich the engine: LIGHTS UP. BUT FAILS TO ACCELERATE SUFFICIENTLY. -An aeroplane equipped with irreversible flight controls: NEED NOT BE EQUIPPED W ITH A SEPARATE GUST LOCK SYSTEM. 2. torsional moment 4. -Aircraft magneto`s receive electrical energy from: ROTATING PERMANENT MAGNETO'S . -An aeroplane equipped with fully powered flight controls (irreversible type): R EQUIRES THE USE OF AN ARTIFICIAL FEEL SYSTEM. -Alternating current can be derived from direct current by: AN INVERTER. -An accumulator in a hydraulic system will: STORE FLUID UNDER PRESSURE. normal bending stresses 2. -An aeroplane whose maximum approved passenger seating configuration is 401 to 5 00 seats must be equipped with at least: 6 HAND FIRE-EXTINGUISHERS CONVENIENTLY LOCATED IN THE PASSENGER COMPARTMENT. -An aeroplane whose maximum approved passenger seating configuration is 301 to 4 00 seats must be equipped with at least: 5 HAND FIRE-EXTINGUISHERS CONVENIENTLY LOCATED IN THE PASSENGER COMPARTMENT. -An aeroplane whose maximum approved passenger seating configuration is greater than 600 seats must be equipped with at least: 8 HAND FIRE-EXTINGUISHERS CONVENIENTLY LOCATED I N THE PASSENGER COMPARTMENT. -An aeroplane whose maximum approved passenger seating configuration is greater than 60 seats must be equipped with at least: 3 HALON 1211 FIRE-EXTINGUISHERS. -An aeroplane whose maximum approved passenger seating configuration is 61 to 20 0 seats must be equipped with at least: 3 HAND FIRE-EXTINGUISHERS CONVENIENTLY LOCATED IN THE PASSENGER COMPARTMENT.-An aeroplane equipped with reversible flight controls: DOES NOT REQUIRE AN ARTI FICIAL FEEL SYSTEM. -An aeroplane whose maximum approved passenger seating configuration is 201 to 3 00 seats must . -An aeroplane whose maximum approved passenger seating configuration is 31 to 60 seats must be equipped with at least: 2 HAND FIRE-EXTINGUISHERS CONVENIENTLY LOCATED IN THE PASSENGER COMPARTMENT. -An aeroplane whose maximum approved passenger seating configuration is 501 to 6 00 seats must be equipped with at least: 7 HAND FIRE-EXTINGUISHERS CONVENIENTLY LOCATED IN THE PASSENGER COMPARTMENT. 2. -An aircraft flying in conditions of continuous heavy rain and high ambient temp eratures may require the precautionary use of: ENGINE IGNITERS. 3. -An aircraft with a pressurized cabin flies at FL 310 and. .be equipped with at least: 4 HAND FIRE-EXTINGUISHERS CONVENIENTLY LOCATED IN THE PASSENGER COMPARTMENT. -An aircraft whose maximum approved configuration for passenger seats is 200 sea ts must be equipped with: 3 HAND FIRE EXTINGUISHERS IN THE COMPARTMENT. Given that: DELTA P: Differential pressure Zc: Cabin altitude: DELTA P WILL RISE UP TO ITS M AXIMUM VALUE. the outflow valve runs to the open position. following a malfuncti on of the pressure controller. T he combination that regroups all of the correct statements is: 1. Given : CAB V/S : Cabin rate of climb indication CAB ALT: Cabin pressure altitude DELTA P: Differential pressure This will result in a: CAB V/S INCREASE CAB ALT INCREASE DELTA P DECREASE -An aircraft with a pressurized cabin is settled at its cruise level. -An artificial feel system: FUNCTIONS IN PARALLEL TO AN IRREVERSIBLE SERVO-CONTR OL UNIT. op ening the primary circuit. -An airplane whose maximum approved passenger seating configuration is 7 to 30 s eats must be equipped with at least: 1 HAND FIRE-EXTINGUISHER CONVENIENTLY LOCATED IN THE PASSENGER COMPARTMENT. 4. 4. During the flight. THUS CAUSING THE SAFETY RELIEF VALVES TO OPEN. -An air cycle machine (air conditioning pack) : CAUSES A PRESSURE AND TEMPERAURE DROP IN THE BLEED AIR. grounding the primary circuit. a malfunction of the pressure controller is detected by the crew and the cabin rate indicator reads 200ft/min. -An aircraft magneto is switched off by: 1. opening the secondary circuit. grounding the secondary circuit. -An engine pressure ratio (EPR) gauge reading normally shows the ratio of: JET P IPE PRESSURE TO COMPRESSOR INLET PRESSURE.-An artificial feel unit is necessary in the pitch channel when: THE ELEVATORS A RE ACTUATED BY IRREVERSIBLE SERVO-CONTROL UNITS. -An electrically heated windscreen is manufactured from: A GLASS AND POLYCARBONA TE LAMINATE. when operating below its design speed. -An engine fire is indicated by a(n): WARNING AND AN AURAL ALERT. -An engine pressure ratio (EPR) can be defined as the ratio of: JET PIPE TOTAL P RESSURE TO COMPRESSOR INLET TOTAL PRESSURE. -An excessively rich mixture can be detected by: BLACK SMOKE FROM EXHAUST. -An engine fire in a large transport aeroplane is indicated by a(n): VISUAL WARN ING AND AN AURAL ALERT. -An axial compressor. . -An EGT (Exhaust Gas Temperature) indicator for a piston engine is used to: ASSI ST THE PILOT TO SET THE CORRECT MIXTURE. -An asymmetric loading (p-factor) on the propeller exists: IF THE AEROPLANE HAS A LARGE ANGLE OF ATTACK. has: A TENDENCY TO STALL IN THE FRONT STAGES. AND. . -An impulse coupling is installed on a magneto of a piston engine to: PROVIDE A STRONGER SPARK ON TOP DEAD CENTRE FOR ENGINE STARTING. THE "O2" LEVER ON NORMAL ALLOWS THE OXYGEN TO ENTER THE REGULATOR AND ENABLES BREATHING OF A MIXTURE OF AIR/OXYGEN ACCORDING TO ALTITUDE.a power lever : ON/OFF . the intake system of a diesel en gine: IS NEVER HEATED BECAUSE A DIESEL ENGINE IS A INJECTION ENGINE. -As altitude increases. -An under-inflated tyre will: EXPERIENCE INCREASED WEAR AT THE SHOULDERS.an "O2" lever : NORMAL/100% . -Apart from flight into known icing conditions. the correct proposition is : THE POWER LEVER ON ON.-An impulse coupling is inhibited at higher than normal rotational starting spee ds by: CENTRIFUGAL FORCE -An impulse coupling is installed on a magneto of a piston engine to: PROVIDE A STRONGER SPARK ON TOP DEAD CENTRE FOR ENGINE STARTING.an emergency lever : ON/OFF Among the following statements. the mixture ratio of a piston engine should be adjusted to : REDUCE THE FUEL FLOW IN ORDER TO COMPENSATE FOR THE DECREASING AIR DENSITY. -An oxygen supply system must be kept absolutely free of oil or grease as: THESE SUBSTANCES CATCH FIRE SPONTANEOUSLY IN THE PRESENCE OF OXYGEN. -An impulse magneto coupling: GIVES A RETARDED SPARK AT STARTING -An inverter is a: unit used to convert dc into ac. -An oxygen regulator has 3 controls : . if flight altitude and air conditioning system setting are maintained: THE MASS AIR FLOW THROUGH THE CABIN IS CONSTANT. the outflow val ve(s) would close.FORK 3HALF FORK 4. If the hy draulic system is then pressurised to its operating pressure of 3000 psi. What will happen if the altitude is decreased while the throttle remains fully open and th e waste gate is seized in the cruise position: THE MANIFOLD ABSOLUTE PRESSURE (MAP) VALUE MAY EXCEED TH E MAXIMUM ALLOWED VALUE.DUAL WHEELS -Assume an initial condition at a high cruise altitude with a constant speed pro peller.CANTILEVER 2 . the CSD should be disconnected : PROVIDED TH E ENGINE IS RUNNING. -Assuming an accumulator is pre-charged with air to 1000 psi and the hydraulic s ystem is pressurised to 1500 psi. the accumulator gauge will read: 1500 PSI. -Assuming cabin differential pressure has reached the required value in normal f light conditions. . if flight altitude is maintained: A CONSTANT MASS AIR FLOW IS PERMITTED THROUGH THE CABIN. the indicated pressure on the air side of the accumulator should be: 3000 PSI. The result would be that: THE PRESSURE DIFFERENTIAL WOULD GO TO THE MAXIMUM VALUE -Assuming a CSD fault is indicated. -Assuming a hydraulic accumulator is pre-charged with air to 1000 psi. -Assume that during cruise flight with airconditioning packs ON.-As the flight altitude increases. -Assuming cabin differential pressure has attained the required value in normal flight conditions. if no leaning is made with the mixture contro l: THE DENSITY OF AIR ENTERING THE CARBURETTOR DECREASES AND THE AMOUNT OF FUEL REMAINS CONSTANT -Associate the correct legend to each of the numbered diagrams : 1. -Assuming the initiating cause is removed. -Assuming the initiating cause is removed. . -Assuming the initiating cause is removed. II IS CORRECT. II IS INCORRECT. A fuse is resettable II. MODULATING THE MIX VALVE. which of these statements about reset ting are correct or incorrect? I. which of these statements about reset ting are correct or incorrect? I. would be accomplished by: THE TEMPERATURE SELECTOR IN CONJUNCTION WITH CABIN SENSORS AND THE TEMPERATURE REGULATOR. which of these statements about reset ting are correct or incorrect? I. -Assuming the jet pipe is not choked. -At constant fuel flow. the cabin rate of climb indicator should ind icate: A RATE OF CLIMB. A circuit breaker is not resettable: I IS INCORRECT. if engine compressor air is bled off for engine anti-ici ng or a similar system. which of these statements about reset ting are correct or incorrect? I. II IS CORRECT. A fuse is not resettable II. A circuit breaker is resettable: I IS INC ORRECT.VV) -Assuming the same swept volume and no turbo charger. the turbine temperature: WILL RISE. II IS INCORRECT. airspeed Vv and jet velocity Vj ) is: T = M(VJ . A circuit breaker is resettable: I IS CORRECT.-Assuming cabin pressure decreases. diesel engines compared to petrol engines: PRODUCE LESS MAXIMUM POWER OUTPUT. -Automatic temperature control of the system as shown. A fuse is not resettable II. -Assuming the initiating cause is removed. A fuse is resettable II. the equation to calculate jet engine thrus t T (with mass flow m. A circuit breaker is not resettable: I IS CORRECT. Which of these statements about a piston engine are correct or incorrect? I. it is often referred to as the: "ANY OR ALL" GATE. -Both gas turbine and piston engines use a cycle made up of induction. compressi on. The process in a gas turbine engine is continuous. II IS CORRECT. Theoretically the combustion occurs at constant pressure: I IS CORRECT. combustion and exhaust phases. combustion and exhaust phases. II IS CORRECT. it is often referred t o as the: "ALL OR NOTHING" GATE. Theoretically the combustion occ urs at constant volume: I IS CORRECT. whilst maintaining thrust. II. Which of these statements about a gas turbine are correct or incorrect? I. -Both gas turbine and piston engines use a cycle made up of induction. isolation of individual equipments: DECREASES THE BUS BAR CURRENT CONSUMPTION. II. -Below its design speed an axial compressor: HAS A TENDENCY TO SURGE IN THE FRON T STAGES. combustion and exhaust phases. -Because of the input/output relationship of an OR gate. compressi on. -Because of the connection in parallel of electrical equipments on an AC bus bar . -Because of the input/output relationship of an AND gate. compressi on. Which of these statements about a piston engine are correct or incorrect? I. i ncreases: EGT AND FUEL FLOW.-Axial piston pumps are often used in hydraulic systems due to: THEIR ABILITY TO PRODUCE HIGH PRESSURE WHEN REQUIRED BUT CAN BE OFF LOADED TO REDUCE POWER CONSUMPTION. -Bleeding air from the HP compressor of a turbofan. The . The process in a piston engine is intermittent. -Both gas turbine and piston engines use a cycle made up of induction. The process in a gas turbine engine is intermittent.. Which of these statements about a piston engine are correct or incorrect? I. compression..Respectively (i) and (ii) are: (I) Continuous (Ii) Constant Pressur e -By-pass ratio in a turbine engine is the ratio of the: COLD AIR MASS FLOW TO TH E HOT AIR MASS FLOW . compressi on... The process in a piston engine is intermittent. Which of these statements about a gas turbine are correct or incorrect? I. II IS INCORRECT.process in a piston engine is continuous. -Both gas turbine and piston engines use a cycle made up of induction... combustion and exhaust phases. -Both gas turbine and piston engines utilise a cycle of induction.. combustion and exhaust phases.and combus tion occurs at (ii). Which of these statements about a gas turbine are correct or incorrect? I. -Both gas turbine and piston engines use a cycle made up of induction.. combustion and exhaust phases. However in the gas turbine these processes are (i).. compressi on. II IS CORRECT. II. II IS INCORRECT. -Both gas turbine and piston engines use a cycle made up of induction. Theoretically the combustion occur s at constant pressure: I IS INCORRECT.. II.. The process in a piston engine is continuous. combustion and exhaust. II. II IS CORRECT. II.. Theoretically the combustion occur s at constant volume: I IS INCORRECT. compressi on. The process in a gas turbine engine is continuous.. II IS INCORRECT. combustion and exhaust phases. II. compressi on. combustion and exhaust phases. -Both gas turbine and piston engines use a cycle made up of induction. Theoretically the combustion occurs at constant volumen: I IS CORRECT. II IS INCORRECT.. Theoretically the combustio n occurs at constant pressure: I IS INCORRECT. Which of these statements about a gas turbine are correct or incorrect? I... The process in a gas turbine engine is intermittent. Theoretically the combustio n occurs at constant volumen: I IS INCORRECT.. -Both gas turbine and piston engines use a cycle made up of induction. compressi on. Theoretically the combustion occ urs at constant pressure: I IS CORRECT. Which of these statements about a piston engine are correct or incorrect? I. II.. -Cabin air for modern aircraft is usually taken from: THE LOW PRESSURE COMPRESSO R AND FROM THE HIGH PRESSURE COMPRESSOR IF NECESSARY. -Cabin differential pressure means the pressure difference between: CABIN PRESSU RE AND AMBIENT AIR PRESSURE. -Cabin pressurisation is regulated by the: CABIN OUTFLOW VALVE(S). -Cabin air for JAR 25 aeroplanes is usually taken from: THE HIGH PRESSURE COMPRE SSOR AND FROM THE LOW PRESSURE COMPRESSOR IF NECESSARY. -Cabin pressure is controlled by: DELIVERING A SUBSTANTIALLY CONSTANT FLOW OF AI R INTO THE CABIN AND CONTROLLING THE OUTFLOW. because: AT HIG H SUBSONIC AIRSPEEDS THEY HAVE A BETTER PROPULSIVE EFFICIENCY THAN PROPELLER OR STRAIGHT JET ENGINES. -Cabin air for a large aeroplane during flight: IS TEMPERATURE CONTROLLED. -Cabin heating in a large jet transport aeroplane is obtained from: HOT AIR BLED FROM THE COMPRESSORS. -Cabin pressurization is controlled by the: CABIN OUTFLOW VALVE. .-By-pass turbine engines are mainly used in commercial aviation. -Cabin altitude is the: CABIN PRESSURE EXPRESSED AS ALTITUDE. They prevent ice formation. -Concerning electrically powered ice protection devices. a tubeless tyre presents the foll owing characteristics: 1 -high heating 2 . smoke hood The combination that regroups all of the correct statements is: 2.. -Compressor surge may be controlled by means of: BLEED VALVES. -Concerning the fuel system high-pressure shut-off valve (HPSOV) of a gas turbin e engine: IGNITION IS ACTIVATED BEFORE FUEL IS DELIVERED BY THE HPSOV TO THE FUEL NOZZLES.valve fragility 3 . -Concerning the sequential pneumatic impulses used in certain leading edge de-ic ing devices. WINDSHIELD. -Compressor stall is due to: AN EXCESSIVELY HIGH ANGLE OF ATTACK OF THE ROTOR BLADES.better adjustme nt to wheels The combination containing all the correct statements is: 3 4 -Compressor stall in a gas turbine engine: CAN BE CAUSED BY AN AXIAL AIRFLOW VEL OCITY THAT IS LOW RELATIVE TO THE ROTOR SPEED..lower risk of bursting 4 . the only true statement is: ON MODERN AEROPLANES. one can affirm that: 1 . -Concerning a constant speed propeller of a twin engine aeroplane controlled by a single-acting pitch control unit: OIL PRESSURE TURNS THE PROPELLER BLADES TOWARDS SMALLER PITCH ANGLE. 2 . 3. cab in 3.-Chemical oxygen generators are used to furnish oxygen to the: 1. ELECTRICALLY POWERED THERMAL DEVICES ARE USED TO PREVENT ICING ON SMALL SURFACES (PITOT-STATIC. 4 -Circuit breakers protecting circuits may be: USED IN AC AND DC CIRCUITS. toilets 4. cockpit 2. -Compared to a tyre fitted with an inner tube.They are triggered from the flight deck after icing .). -Consider a jet engine whose control is based on the Engine Pressure Ratio (EPR) : 1. in the event of icing not detected by the crew. During deceleration: WHE N BRAKING. 3. 4 . with a constant EPR. The combination that regroup s all of the correct statements is: 1. The combination which regroups all the correct statements is: 2 3 -Concerning the starting procedure of a gas turbine engine: THE SELECTED IGNITER S ARE ACTIVATED AFTER FUEL IS DELIVERED TO THE FUEL NOZZLES.There are more than ten cycles per second. -Cooling air for a reciprocating engine can be obtained by means of: RAM AIR -Creep in a gas turbine engine is: THE PERMANENT INCREASE IN LENGTH OF METAL PAR TS DUE TO A COMBINATION OF TENSILE STRESS AND HIGH TEMPERATURES OVER A PROLONGED PERIOD. THE PROPELLER SUPPLIES NEGATIVE THRUST AND ABSORBS ENGINE POWER. 2. 4. . -Connecting two 12 volt 40 ampere-hour capacity batteries in series will result in a total voltage and capacity respectively of: 24 VOLTS. At same environmental conditions. the indicated EPR is lower than the rea l EPR The combination regrouping all the correct statements is: 1. the EPR is de termined by the impact pressure difference between the turbine outlet and the compressor inlet 5 . -Consider the variable-pitch propeller of a turbo-prop. 3. 40 AMPERE-HOURS. locating a balancing mass in front of t he control hinge.A cycle lasts more than ten seconds. -Continuous loop fire detector systems operate on the principle that an increase in temperature produces: A DECREASE IN RESISTANCE -Control surface flutter can be avoided by: 1. a high torsional stiffness of the structure. a given EPR setting maintains the thrust irrespective of engine wear due to ageing. the thrust is independent of the Mach number 3. 3. on take-off. 4. with a constan t EPR. the thrust decreases when the altitude increases 2. a low torsional stiffness of the structure. 3 .has become visible. locating a balancing mass behind the control hinge. -Direct current generators are connected: IN PARALLEL TO PROVIDE MAXIMUM POWER. because: THE FUEL DROPL ETS COMING FROM THE ATOMISER DO NOT BURN COMPLETELY.-Creep of turbine blades is caused by: HIGH BLADE TEMPERATURE WHILST UNDER CENTRIFUGAL LOADING. -During flight. -Dual ignition provides a factor of reliability and: IMPROVES COMBUSTION EFFICIE NCY. -During hydroplaning. compared to petrol engines have: A HIGHER COMPRESSION RATIO. -Derated or reduced take-offs save engine life primarily due to: REDUCED LOW CYC LE FATIGUE DAMAGE. -Diesel engines always produce a certain amount of soot. -During a climb in a standard atmosphere with constant Manifold Absolute Pressur e (MAP) and RPM indications and at a constant mixture setting. the wing anti-ice system has to protect: A PART OF THE WHOLE LEA DING EDGE. -During a normal pressurised climb after take-off: CABIN PRESSURE DECREASES MORE SLOWLY THAN ATMOSPHERIC PRESSURE -During climb with constant throttle and RPM lever setting (mixture being consta nt) the: MANIFOLD ABSOLUTE PRESSURE (MAP) DECREASES. -Diesel engines. the friction coefficient between tyre and runway surface i s approximately: 0 . the power output of a piston engi ne: INCREASES. by freefall. 2. by mechanical/manual means. the fan in a high by-pass ratio turbofan engine produces: THE GREATER PART OF THE THRUST. optimised for cruise condition is: RELATIVELY HIGH. protect the aircraft against l ightning effects. set the aircraft to a single potential The combin ation regrouping all the correct statements is: 1. the angle of attack of the blades of a fixed pitch propeller. 2. the cabin outflow valves are: PARTIALLY OPEN. . reset the electrostatic potential of the aircraft to a value approximating 0 volt 3. 5 . reduc e radio interference on radio communication systems 4. 4. 5. 3. 3. with compressed oxygen.-During level flight at a constant cabin pressure altitude (which could be decre ased. the generator is activated by: A SET OF PERMANENT MAGNETS. The combination that regroups all of the correct statements is: 2. -During take-off. -During the ram recovery process in a gas turbine engine subsonic intake. -During start of an engine fitted with a brushless AC generator with no commutat or rings. -Emergency extension of landing gear systems can be performed:: 1. 4 -Electrically powered ice protection devices on aircraft are: USED AS ANTI-ICING DEVICES FOR PITOT-TUBES. -Electrical bonding of an aircraft is used to: 1. 4. with compress ed C0². -During re-fuelling the automatic shut-off valves will switch off the fuel suppl y system when: THE FUEL HAS REACHED A PREDETERMINED VOLUME OR MASS. STATIC PORTS AND WINDSHIELD. even at this flight level). the: F LOW VELOCITY DECREASES. with compressed nitrogen. -During take-off. -Evacuation slide normal inflation is achieved by: A PRESSURISED GAS CANISTER. 4. -Exhaust gas temperature sensing is usually taken: BETWEEN THE GAS GENERATOR TUR BINE AND THE FREE POWER TURBINE. . 3. it drains th e carburettor float chamber 2. -Engine compartment decking and firewalls are manufactured from: STAINLESS STEEL OR TITANIUM SHEET. -Engine bleed air used for air conditioning and pressurization in turbo-jet aero planes is usually taken from the: COMPRESSOR SECTION. -Engine temperature limitations of a gas turbine engine are usually imposed due to temperature limitations on the: TURBINE SECTION. the risk of engine fire. The combination that regroups all of the correct statements is: 2. -Excessive priming of a piston engine should be avoided because: 1.-Engine auxiliary gearboxes: PROVIDE THE DRIVES FOR A WIDE VARIETY OF SERVICES A ND MAY EVEN PROVIDE FOR THE SUPPORT OF THE ENGINE IN THE AIRFRAME. 4. -EPR can be defined as the ratio of: THE TOTAL TURBINE OUTLET PRESSURE TO THE TO TAL COMPRESSOR INLET PRESSURE. 3. -Excessive pressure in the cylinders of an engine equipped with a constant speed propeller: HIGH MANIFOLD PRESSURE AND LOW RPM. it fo uls the spark plugs. -Engine temperature limitations are usually imposed due to temperature limitatio ns on the: TURBINE SECTION. the risk of flooding the engine. -Filters in hydraulic systems often incorporate pop out indicators to: WARN OF A N IMPENDING BY-PASS SITUATION. i n the event of depressurisation. 2. -Flutter results from two deformation modes which are: TORSION AND BENDING -For a fan jet engine.4 -Fixed-pitch propellers are usually designed for maximum efficiency at: CRUISING SPEED -Flat rated jet engines are designed to provide constant maximum take-off thrust up to a certain level of: AMBIENT TEMPERATURE. The combination of corrects statem ents is: 1. during a no rmal flight. 3. -Filtration in a hydraulic system is usually ensured by: FILTERS IN BOTH THE PRE SSURE AND RETURN LINES. . -For a fan jet engine. -Fire precautions to be observed before refuelling are: ALL BONDING AND CONNECTI ONS TO THE EARTH TERMINAL BETWEEN GROUND EQUIPMENT AND THE AIRCRAFT SHOULD BE MADE BEFORE FILLER CAPS ARE REMOVED. the by-pass ratio is the: COLD AIR MASS FLOW DIVIDED BY T HE HOT AIR MASS FLOW. -Fixed oxygen systems in pressurised aeroplanes are used to provide oxygen: 1. 4. in the event of any passenger indisposition. in the event of smoke or toxic fumes in the cockpit. the by-pass ratio is the: EXTERNAL AIRFLOW MASS DIVIDED B Y THE INTERNAL AIRFLOW MASS -For a free power turbine engine: THE TURBINE DRIVING THE MAIN ROTOR TRANSMISSIO N IS MECHANICALLY INDEPENDENT FROM THE GAS GENERATOR. -For a turbine engine. provided it is strong enough. -For a subsonic airflow. the term self-sustaining speed relates to the lowest rpm range at which the engine: WILL CONTINUE TO RUN WITHOUT ANY FURTHER STARTER ASSISTANCE. THEIR DEFLECTI ON CAN BE SYMMETRICAL OR ASYMMETRICAL. -For a JAR25 aeroplane. the oil viscosity depends on the: OIL TEMPERATURE. 4. 2. air passing through a divergent duct: DECREASES IN VELO CITY AND INCREASES IN PRESSURE. THE PRESSURE RELIEF VALVES.-For a given type of oil. -For a turbine engine. The combination that regroups all of the correct state ments is: 1. -For a subsonic airflow. the chemically correct fuel/air ratio is: 1:15 -For a reciprocating engine fuel/air ratio or mixture is the ratio between the: MASS OF FUEL AND MASS OF AIR ENTERING THE CYLINDER. -For an aeroplane hydraulic supply circuit. the design is bas ed on the principle of redundancy of components. spoilers are: UPPER WING SURFACE DEVICES. -For fail safe designed structural components: 1. AND THE FIRE SHUT-OFF VALVE. one load carrying component is sufficient. the self-sustaining speed relates to the minimum RPM at w hich the engine: WILL CONTINUE TO OPERATE WITHOUT ANY STARTER MOTOR ASSISTANCE. VELOCITY D ECREASES AND TEMPERATURE INCREASES. there is more than one load ca rrying component. -For a piston engine. the component is removed at the end of the calculated life time or number of cycles. in a divergent duct the: PRESSURE INCREASES. . the correct statement is: THE SECURI TY COMPONENTS COMPRISE THE FILTERS. 4. 3. THE BY-PASSES. -Fuel pumps submerged in the fuel tanks of a multi-engine aircraft are: CENTRIFU GAL LOW PRESSURE TYPE PUMPS. to maintain the same mixture the fuel flow should: INCREASE -Fuel flow information for gas turbine engines is: MEASURED IN THE LINE BETWEEN THE FUEL CONTROL UNIT AND THE ENGINE BURNERS. mixture ratio is the ratio between the: MASS OF FUEL AND MA SS OF AIR ENTERING THE CYLINDER. with all the parameters correctly set. 3. reciprocating engines are especially dependent on: THE CI RCULATION OF LUBRICATING OIL -For most large aeroplanes. -For take-off. one load carrying component is sufficient for a given load. -For safe life designed structural components : 1. provided it is stron g enough.-For internal cooling. The combination that regroup s all of the correct statements is: 2. the correct combination of propeller pitch (1). . -Fuel for gas turbine engines is usually heated in order to: PREVENT ICING-UP OF THE LP FILTER. and propeller lev er position (2) at brake release is: (1) LOW (2) FORWARD. -For piston engines. there is more than one load c arrying component. spoilers are: UPPER WING SURFACE DEVICES AND THEIR DEFLECTION CAN BE SYMMETRICAL OR ASYMMETRICAL. the design is based on the principle of redundancy of components. 2. the component is removed at the end of the calculated life time or number of cycles. 4. -From the cruise. 3. if the altitude is redu ced. The combination .exhaust nozzle gas velocity150 m/s .-Generally. when the fire handle of the engine fire-extinguishing system on an a eroplane is pulled. 2. -Generators. The combination that regroups all of the correct statements is: 2. Net engine thrust equals: 3500 N. the effects are: 1. electrical heating for ice protection is used on: PITOT TUBES.cross-sectional area of the nozzle 0. how is control ma intained if one hydraulic system is lost due to a hydraulic leak? THE REMAINING SYSTEMS WILL TAK E OVER CONTROL. -Given a conventional transport aeroplane with irreversible flight controls on t he ground with engines running. THE RUDDER PEDALS MOVE IN THE CORRESPONDING DIRECTION. for large aeroplanes. on modern jet transport aircraft. 5 diesel fuel is less inflammable than petrol. when connected to the same bus bar. -Given an aeroplane with irreversible primary flight controls. 2 there is no mixture control. The combination th at regroups all of the correct statements is: 2. 5 diesel fuel is more inflammable than pet rol. 1 power is regulated by th e throttle valve. 4 thermal efficienc y is lower than that for a petrol engine.10 m. -Given the following information about an aeroplane with a turbojet engine: . -Generally.ma ss air flow 50 kg/s TAS 90 m/s . 4. opening of the bleed air valves and HP valves on the engine concerned.exhaust nozzle static pressure1050 hPa ambient static pressure 1000 hPa . 3 power is set by the fuel flow. immediate discharge of extinguishing agent. Which of these statements about rudder trim actuation is correct? THE R UDDER MOVES. d eactivation of the electric generators. 3 the amount of power is determined by the fuel flow only. arming of the extinguishing system. 5. 3. 3. 2 there is no throttle valve. 4 thermal efficiency is higher than that for a petrol engine. -Given the following statements about diesel engines. are usually connected: IN PARAL LEL MODE. 4. how can the landing gear be extend ed if there is a complete hydraulic system failure: MECHANICALLY -Generally. -Given the following statements about diesel engines: 1 power is set by the mixt ure control. entering the hydraulic pump. high compressibility 6. -Hydraulic power is a function of: SYSTEM PRESSURE AND VOLUME FLOW. good resistance to combustion 5.that regroups all of the correct statements is: 2. 4 -Hydraulic fluids used in systems of large modern airliners are: PHOSPHATE ESTER BASE FLUIDS. is slightly pressurised to: PREVE NT CAVITATION IN THE PUMP -Hydraulic fluids must have the following characteristics: 1. thermal stability 2. low emulsifying characteristics 3. -Hydraulic fluid.P0). corrosion resistance 4. -Given: p0 = static ambient pressure t0 = static ambient temperature m = air mas s flow Vv = True Air Speed Vj = jet efflux (exhaust) velocity pj = jet efflux (exhaust) static pressu re tj = jet efflux (exhaust) static temperature A = exhaust cross-sectional area The thrust T of a jet engine is: T = M(VJ -VV ) + A(PJ . -Halon is used as a fire extinguishing agent because it: ACTS AS A VERY EFFECTIV E FLAME INHIBITOR. 3. . -Ice formation on turbofan engine intakes is usually: PREVENTED BY USING COMPRES SOR BLEED AIR. high viscosity The combination regrouping all the correct sta tements is : 1. high volatility 7. -If a current is passed through a conductor which is positioned in a magnetic fi eld: A FORCE WILL BE EXERTED ON THE CONDUCTOR.3.4. 2. -Hydraulic fluids: ARE IRRITATING TO EYES AND SKIN. -If an engine fails to stop with the magneto switch in OFF position. the battery: IS UNSERVIC EABLE. -If a twin spool gas turbine engine is controlled by a conventional N2 control s ystem. -If an engine detonates during climb-out.-If a gas turbine engine fuel/oil heat exchanger is located downstream of the HP fuel pump. -If an abortive start (hung start) occurs when starting a gas turbine engine. internal leakage of the heat exchanger will cause the oil level to: RISE. rupture of the LP shaft may result in: OVERSPEED OF THE LP TURBINE. the e ffect on the engine pressure ratio (EPR) and the exhaust gas temperature (EGT) is that: EPR DECREASE S AND EGT INCREASES. -If air is tapped from a gas turbine HP compressor. -If the cabin altitude rises (aircraft in level flight). the turbine temperature: WILL RISE. th e correct action is to: SHUT DOWN THE ENGINE. the effect on the engine pre ssure ratio (EPR) and the exhaust gas temperature (EGT) is that: EPR DECREASES AND EGT INCREASES. -If air is tapped from a gas turbine HP compressor (engine N2 controlled). -If one of the 12 cells of a lead-acid battery is dead. the cause m ay be: EXCESSIVE CARBON FORMATION IN CYLINDER HEAD. the differential pressu re: DECREASES . -If engine compressor air is bled off for engine anti-icing or a similar system. the normal corrective action would be to: RETARD THE THROTTLE. -If the engine. -If the manifold pressure is increased. is detonating during climb-out aft er takeoff. -If the pressure in the cabin tends to become lower than the outside ambient air pressure the: NEGATIVE PRESSURE RELIEF VALVE WILL OPEN. with a fixed pitch propeller. the normal corrective action would be to: REDUCE THE THROTTLE -If the ground wire between the magneto and the ignition switch becomes disconne cted.-If the electrical load of an AC generator providing a constant output voltage i ncreases. -If there is a single input data failure on a FADEC gas turbine engine: THE ENGI NE CONTINUES TO . -If the maximum operating pressure of the oxygen system is exceeded the: OXYGEN IS DISCHARGED OVERBOARD VIA A SAFETY PLUG. oil to the main bearings is still assured: BECAUSE THE OIL FILTER BYPASS VALVE OPENS. -If the ground wire between the magnetos and the ignition switch becomes disconn ected the most noticeable result will be that: THE ENGINE CANNOT BE SHUT DOWN BY TURNING THE IGNITION SWITCH TO THE "OFF" POSITION. the voltage regulator will: INCREASE THE INTENSITY OF THE EXCITATION CURRENT. -If the main oil filter of a gas turbine engine becomes clogged. this limitation is due to the maximum: POSITIVE CABIN DIFFERENTIAL PRESSURE AT MAXIMUM CABIN ALTITUDE. the most noticeable result will be that the engine: CANNOT BE SHUT DOWN BY TURNING THE SW ITCH TO THE OFF POSITION. the blade angle of a constant speed prop eller : IT WILL INCREASE -If the maximum operating altitude of an aeroplane is limited by the pressurized cabin. PASSED THROU GH A SECONDARY HEAT EXCHANGER. -If two constant frequency AC generators are operating independently. then the p hase relation between both generators: IS UNIMPORTANT. -In a bootstrap cooling system the supply air is first: COMPRESSED. THE GROUNDING WIRE IS B ROKEN. an ammeter showing a high charge rate to the battery: WOULD BE NORMAL AND IS ONLY CAUSE FOR CONCERN IF THE HIGH CHARGE RATE PERSISTS. -Ignition occurs in each cylinder of a four stroke engine (TDC = Top Dead Centre ): BEFORE TDC AT EACH SECOND CRANKSHAFT REVOLUTION. the most probable cause is that: THE GROUNDING WIRE OF ONE OF THE MAGN ETOS IS BROKEN. a piston engin e continues to run normally. the mass air flo w is routed via the: SECONDARY HEAT EXCHANGER OUTLET TO THE TURBINE INLET OF THE COLD AIR UNIT. the most probable cause is that: ON A MAGNETO. AND THEN ACROSS AN EXPANSION TURBINE. when the magneto selector switch is set to the OFF position. -In a cabin air conditioning system. the charge air is first compressed in the cold air unit to: ENSURE AN ADEQUATE PRESSURE AND TEMPERATURE DROP ACROSS THE COOLING TURBINE. -In a "bootstrap" cooling system. -Ignition systems of a running piston engine receive electrical energy from: ROT ATING PERMANENT MAGNETS. a piston engin e continues to run normally. equipped with a bootstrap. -If. .OPERATE NORMALLY. when the magneto selector switch is set to the OFF position. -If. -Immediately after starting engine(s) with no other electrical services switched on. if the axial air velocity increases more than the rotor blade velocity the: STALL MARGIN INCREASES. -In a four-stroke piston engine. the contents gaug e of a half-full fuel tank indicates a fuel mass of 8000 kg. -In a gas turbine combustion chamber: SECONDARY AIR IS REQUIRED FOR COOLING OF T HE INNER CASING. -In a compressor stage of a jet engine. the only "driving" stroke is: POWER -In a free turbine engine. . -In a gas turbine engine lubrication system. -In a fire detection system with single-loop continuous components (with no faul t protection). the sequence is: ROTOR STATOR -In a compressor stage. -In a free turbine engine: THERE IS NO MECHANICAL CONNECTION BETWEEN THE COMPRESSOR AND THE POWER OUTPUT SHAFT. If a temperature rise increased the volum e of fuel by 5%. the energy delivered by the free turbine stages: IS D EPENDENT ON THE ROTATIONAL SPEED OF THE GAS GENERATOR. -In a compensated capacitance type quantity indicating system. the oil to fuel heat exchanger prov ides: OIL COOLING THROUGH THERMAL EXCHANGE WITH THE FUEL.-In a commercial transport aeroplane the landing gear normal operating system is usually: HYDRAULICALLY DRIVEN. if the line is accidentally grounded: THE FIRE ALARM IS TRIGGERED. the indicated fuel mass would: REMAIN THE SAME. the maximum gas temperature is attained: WITHIN THE CO MBUSTION CHAMBER. will read: 3000 PSI -In a hydraulic system overheat detectors are mostly installed: AT THE PUMPS. -In a gas turbine engine.-In a gas turbine engine the creep phenomenon is the most severe in the: TURBINE ROTORS. which are not rigidly fixed in posi tion when the engine is stationary. -In a hydraulic system. the propelling jet is generated by: EXPANSION OF HOT G ASES RESULTING IN A CONVERSION OF POTENTIAL ENERGY (PRESSURE) INTO KINETIC ENERGY (VELOCITY). -In a modern hydraulic system. . an accumulator is pre-charged to 1200 psi. "hydraulic fuses" can be found. the pressu re gauge. which is connected to the gas section of the accumulator. -In a gas turbine engine. the reservoir is pressurized in order to: PREVENT PUMP C AVITATION -In a jet engine the propelling nozzle: MUST BE DESIGNED TO OBTAIN THE CORRECT BALANCE OF PRESSURE AND VELOCITY TO PREVENT FLOW SEPARATION. the power changes are normally made by controlling the amount of: FUEL SUPPLIED. If an electrically driven hydraulic pump is started and provides a system pressure of 3000 psi. compressor blades. Their function is : TO PREVENT TOTAL SYSTEM LOSS IN CASE OF A LEAKING HYDRAULIC LINE. -In a hydraulic braking system. -In a gas turbine engine. -In a gas turbine engine. take up a rigid position when the engine is running due to: THE RESU LTANT OF AERODYNAMIC AND CENTRIFUGAL FORCES. -In a pressurized aircraft whose cabin altitude is 8000 ft. the purpose of an altitude mixture control is to: CORRECT F OR VARIATIONS IN THE FUEL/AIR RATIO DUE TO DECREASED AIR DENSITY AT ALTITUDE. -In a piston engine. turbocharger boost pressure may be monitored by: A MANIFOLD PRESSURE GAUGE ONLY. -In a piston engine. a crack in a cabin w indow makes it necessary to reduce the differential pressure to 5 psi. -In a single spool gas turbine engine. PRESSURE DECREASES AND TEMPERATURE DECREASES . -In a subsonic convergent duct the: VELOCITY INCREASES. -In a piston engine if the ratio of air to fuel is approximately 9:1 the mixture is: RICH. the compressor rpm is: THE SAME AS TURBIN E RPM. the protective breathing equipment: PROTEC TS THE MEMBERS OF THE CREW AGAINST FUMES AND NOXIOUS GASES. the fan is driven by: THE REARMOST TURBINE. magnetos are used to produce the spark which ignites the fu el/air mixture. the only "driving" stroke is the: POWER STROKE. The operating principle of magnetos consists in : BREAKING THE PRIMARY CURRENT IN OR DER TO INDUCE A LOW AMP HIGH VOLT CURRENT WHICH IS DISTRIBUTED TO THE SPARK PLUGS. The flight level to be m aintained in order to keep the same cabin altidue is: FL 230 -In a pressurized transport aircraft.-In a multi-spool turbofan engine. -In a reciprocating four-stroke engine. -In a piston engine. -In a turbo compressor air conditioning system (bootstrap system). PASSED THR OUGH A SECONDARY HEAT EXCHANGER. 100 % of the passengers in a non-pressurized airpla ne must have an oxygen supply reserve for the entire flight time at pressure altitudes greater t han: 13000 FT. the purpose o f the heat exchangers is to: COOL THE BLEED AIR IN FRONT AND BEHIND THE COMPRESSOR OF THE AIR CYCLE MACHINE. -In addition to the fire hazard introduced. -In accordance with JAR-OPS. the purpose of the turbine is to: DRIVE THE COMPRESSOR BY USING PART OF THE ENERGY FROM THE EXHAUST GASES -In a typical bootstrap cooling system the supply air is: COMPRESSED. excessive priming should be avoided because:IT WASHES THE LUBRICANT OF CYLINDER WALLS . air may be ble d from compressors of a turbofan engine to increase stall margin: AT LOW ROTOR SPEED. -In addition to providing 'customer' bleed for aeroplane systems. -In a turbo compressor air conditioning system (bootstrap system) the supply of air behind the primary heat exchanger is: COMPRESSED.-In a theoretical gas turbine cycle. -In a turbo-jet. AND THEN ACROSS AN EXPANSION TURBINE. the main wate r separation unit is: AFTER THE COOLING TURBINE. AND THEN ACROSS AN EXPANSION TURBINE. PASSED THROUGH A HEAT EXCHANGER. -In a turbo compressor air conditioning system (bootstrap system). combustion takes place at constant: PRESSUR E. -In accordance with JAR-OPS. 10 % of the passengers in a non-pressurized airplan e must have an oxygen supply reserve for the entire flight time when the cabin altitude pressur e is greater than: 10000 FT BUT NOT EXCEEDING 13000 FT MINUS 30 MINUTES. can be dis connected from the engine shaft. -In an aircraft electrical system where AC generators are not paralleled mounted .-In an AC power generation system. 2. 3. 3.is an electronic system. the low temperature that c auses carburettor ice is normally the result of: VAPORIZATION OF FUEL AND EXPANSION OF THE AIR IN THE CARBURETOR -In an ignition system during a normal start of a gas turbine engine. -In an aircraft air conditioning system the air cannot be treated for: HUMIDITY. The combination regrouping all the correct statements is : 1. the changeover relay allows: POWER SUPPLY TO THE FAULTY AC GENERATORS BUSBAR. AC for instrument operatio n may be obtained from: AN INVERTER. -In an engine equipped with a float-type carburettor. the Constant Speed Drive (CSD): 1. -In an aircraft equipped with a DC main power system. DC power is o btained from a: TRANSFORMER RECTIFIER UNIT (TRU). 6 -In an aeroplane fitted with a constant frequency AC power supply. 4. 6.can be disconnect ed in flight. igniter ac tivation: SHOULD COMMENCE PRIOR TO FUEL ENTERING THE COMBUSTION CHAMBER. 5. -In an alternator rotor coil you can find : AC.can not be disconnected in flight. -In an air cycle machine: THE TURBINE DRIVES THE COMPRESSOR OF THE MACHINE WHICH CAUSES A HIGHER TEMPERATURE. .can be disconnected from the generator. AND SO INCREASES THE SECOND HEAT EXCHANGER EFFICIENCY.is a hydro-mecha nical system. the cabin air for large jet transport aeroplanes is usually supplied by: ENGINE COMPRESSORS. -In case of smoke in the cockpit. not fitted with feathering system: MOVE IN THE LOWEST PITCH POSITION BY THE CENTRIFUGAL FORCE AND/OR THE SPRING FORCE. the reflection on ionosphere layers phenomenon is used in the foll owing frequencies: HF -In case of engine failure during flight the blades of a constant speed propelle r in a single engine aeroplane. the crew oxygen regulator must be set to: 100% -In computer technology. an output peripheral is a: SCREEN UNIT.-In an on-board computer. if the constant speed drive (CSD) temperature indicator is in the re d arc the: PILOT MUST DISCONNECT IT. EEPROM. -In flight.) -In aviation. a cantilever wing of an aeroplane containing fuel is subjected to ve rtical loads that produce a bending moment. the software is: RESIDENT IN A READ-ONLY MEMORY (REPRO M. a storage peripheral is a: HARD DISK DRIVE -In computer technology. AND THE GENERATOR IS NOT AVAILABLE FOR THE REST OF FLIGHT... which is: HIGHEST AT THE WING ROOT. . -In flight.. not fitted with feathering system: MOVE IN THE LOWEST PITCH POSITION BY THE CENTRIFUGAL FORCE AND/OR THE SPRING FORCE. -In case of engine failure during flight the blades of a constant speed propelle r in a single engine aeroplane. -In flight. -In computer technology. an input peripheral is a: KEYBOARD. in the air conditioning system. oxygen for the flight deck oxygen system is stored as a: GAS. breathing oxygen for the cockpit is stored in the fo llowing state: GASEOUS -In large modern aircraft. -In order to produce an alternating voltage of 400 Hz. -In flight. -In flight. -In jet aeroplanes the 'thermal anti-ice system' is primarily supplied by: BLEED AIR FROM THE ENGINES. the cabin air for modern airplanes with jet engines is usually suppl ied by: ENGINE COMPRESSORS. -In hydraulic systems of large modern transport category aircraft the fluids use d are: SYNTHETIC OIL. -In order that DC generators will achieve equal load sharing when operating in p arallel. Rebalancing of the two tanks is: POSSIBLE WITH "CROSSFEED " OPEN AND TANK 1 PUMPS "OFF" AND TANK 2 PUMPS "ON". with centre tank empty and APU operating. a fuel unbalance is detect ed (quantity in tank 1 < quantity in tank 2). reduction of air temp erature and pressure is achieved by: AN EXPANSION TURBINE. it is necessary to ensure that: THEIR VOLTAGES ARE ALMOST EQUAL. -In jet transport aircraft. -In jet transport aeroplanes. the most commonly used anti-icing method for the wings of modern com mercial aircraft fitted with turbo-jet units is: THERMAL (USE OF HOT AIR). the number of pairs of po les required in an AC generator running at 6000 rpm is: 4 .-In flight. the bandwidth is: THE FREQUENCY BAND .-In regard to passengers briefing in public transport aeroplane. at least one manual fire-extinguisher m ust be conveniently located containing : HALON. the axial ve locity of the air is greatest: ON EXIT FROM THE PROPELLING NOZZLE. -In the axial flow compressor of a turbo-jet engine. I ts shape is calculated so as to: MAINTAIN A CONSTANT AXIAL SPEED IN CRUISING FLIGHT. -In straight and level flight the most important loads on a cantilever wing are: COMPRESSION IN THE UPPER SURFACE. on a twin engine aeroplane. -In some aircraft. this demonstration must be completed before: TAKE-OFF. -In the airflow through a single-spool axial flow turbo-jet engine. It consists of: A LATCH LOCATED IN THE LANDING GEAR LEVER. -In the event of an AC generator fault. what balancing Force would be actin g on the left hand side ? (The diagram is not to scale): 100 N. DUE TO THE COMBINATION OF THE SKY AND GROUND WAVES. the phenomenon of FADING is particularly found: AT NIGHT. TENSION IN THE LOWER SURFACE. -In the response curve of an amplifier. -In the cockpit of a transport airplane. -In the hydraulic press schematically shown. -In the propagation of MF waves. the flow duct is tapered. If a flight is to be carried out at FL 290. there is a protection device to avoid the landing gear being inadvertently retracted on the ground. the protecti on device will open: THE EXCITER CONTROL RELAY AND THE GENERATOR BREAKER. information abo ut oxygen must be given to passengers through a demonstration. PS DECREASES.CORRESPONDING TO MAXIMUM GAIN LESS 3 DECIBELS. assuming hydraulic pressure throughout and no internal leakage: A CONDITION OF HYDRAULIC LOCK EXISTS AND NO MOVEMENT OF THE PISTON WILL TAKE PLACE. IF IT DECREASES AFTER STARTUP. IF IT DECREASES AFTER STARTUP. -In twin-engine aeroplanes with right turning propellers: THE LEFT ENGINE IS THE CRITICAL MOTOR. -In the typical hydraulic system represented in the graphic. -In very cold weather. This higher pressure: IS NORMAL. -In very cold weather. a slightly higher than normal engine oil pressure during startup: IS ACCEPTABLE. a slightly higher than normal engine oil pressure. the pilot notices during startup. -In what state is the breathing oxygen for the cockpit of jet transport aeroplan es stored: GASEUS -In which part of a gas turbine engine are high temperature requirements most cr itical for the materials used? THE COMBUSTION CHAMBER AND FRONT PART OF THE HP TURBINE. -In the stator of a turbine. -In which sections of the carburettor would icing most likely occur? VENTURI AND THE THROTTLE VALVE -Increasing the frequency of variations in thrust setting during normal operatio n is detrimental to the life of HP turbine blades because: LOW CYCLE FATIGUE DAMAGE IS MORE SEVERE. . the gas velocity V and static pressure Ps vary as f ollows: V INCREASES. -Main cabin temperature is: CONTROLLED AUTOMATICALLY. -Landing gear torque links are used to: PREVENT ROTATION OF THE LANDING GEAR PIS TON IN THE OLEO STRUT. -Maximum exhaust gas temperature (EGT) of a piston engine is theoretically assoc iated with a: FUEL TO AIR RATIO OF 1:15. ALLOWING SOME MOVEMENT BETWEEN ROTATING AND STATIC PARTS.-Increasing the power setting of a gas turbine engine with a constant speed prop eller and free power turbine causes: BOTH HP SPOOL SPEED AND EGT TO INCREASE. -Labyrinth seals in the lubrication system of a gas turbine engine are designed to provide a seal that is: NOT COMPLETELY TIGHT. -Maximum power output and low mass of aeroplane hydraulic systems can be achieve d with: HIGH SYSTEM PRESSURE AND LOW VOLUME FLOW. -Internal leakage in a hydraulic system will cause: AN INCREASED FLUID TEMPERATU RE. . -Jet engine total efficiency indicates the efficiency at which: CHEMICAL POWER I N THE FUEL IS TRANSFORMED INTO PROPULSIVE POWER (T X V). -Large transport aeroplane hydraulic systems usually operate with a system press ure of approximately: 3000 PSI -Loads on the cylindrical part of the fuselage during pressurisation are carried by the: SKIN. OR BY FLIGHT CREW SELECTION. A. THE OTHER THE CABIN. -On a FADEC gas turbine engine during normal flight. . Is it still possible to trim these control surfaces? YES. TRIMMING IS POSSIBLE BY ADJUSTING THE NEUTRAL POINT OF THE ARTIFICIAL FEEL MECHANISM BY MEANS OF A TRIM SWITCH.E. -On a 13653 a fire detection system includes: A WARNING LIGHT FOR EACH ENGINE AN D A SINGLE ALARM BELL COMMON TO ALL ENGINES -On a a normally aspirated engine (non turbo-charged). it is normal for reverse thrust to be achieved by reversing: ONLY THE DIRECTION OF THE FAN AIRFLOW.C. the power for the FADEC's s ensors comes from: THE FADEC POWER SOURCE(S) ON THE ENGINE. This means that: THE FLIGHT CONTROL SYSTEM HAS PROVISIONS TO DISCONNECT THE PART OF THE CONTROL SYSTEM THAT BECOMES BLOCKED. the meaning of F. -On a FADEC jet engine. ONE SUPPLYING THE COCKPIT.-Modern pressurized transport aeroplanes are equipped with: TWO INDEPENDENT OXYG EN SYSTEMS. -On a high by-pass ratio (fan) engine. the manifold pressure gau ge always indicates: A LOWER VALUE THAN ATMOSPHERIC PRESSURE WHEN THE ENGINE IS RUNNING.D. -Most high-bypass (unmixed) turbofan engines are equipped with a cold exhaust re verser (fan reverser) only in order to: SAVE COSTS AND MASS AT THE EXPENSE OF A REDUCTION IN AVAILABLE REVERSE THRUST. due to the distribution of the thrust. on a gas turbine engine is: FU LL AUTHORITY DIGITAL ENGINE CONTROL. -Most large conventional aeroplanes are not provided with aileron and rudder tri m tabs. -Most transport aeroplanes are provided with protection against control jamming. due fo r example to prolonged braking during an aborted take-off. the maximum cabin differentia l pressure is approximately: 7 . the auto-slat system: EXTENDS (PART OF) THE SLA TS AUTOMATICALLY WHEN A CERTAIN VALUE OF ANGLE OF ATTACK IS EXCEEDED. reverse thrust is achieved by reversing: ONLY THE DIRECTION OF THE FAN AIRFLOW. -On a modern aeroplane. the manifold pressure gauge always indicates: A LOWER VALUE THAN ATMOSPHERIC PRESSURE WHEN THE ENGINE IS RUNNING. -On a large transport aeroplane. -On a jet aircraft fuel heaters are: LOCATED ON THE ENGINES. . to avoid the risk of tyre burst from overheating. -On a modern large pressurized transport aircraft. -On a normally aspirated engine.9 PSI -On a multi-engined aircraft a fire detection system includes : A WARNING LIGHT FOR EACH ENGINE AND A SINGLE ALARM BELL COMMON TO ALL ENGINES -On a non-stressed skin type wing.-On a high by-pass ratio (fan) engine. there is: A HOLLOW BOLT SCREWED IN TO THE WHEEL WHICH MELTS AT A GIVEN TEMPERATURE (THERMAL FUSE) AND DEFLATES THE TYRE. the wing structure elements which take up the vertical bending moments Mx are: THE SPARS. -On a normally aspirated aero-engine fitted with a fixed pitch propeller: MANIFO LD PRESSURE DECREASES AS THE AIRCRAFT CLIMBS AT A FIXED THROTTLE SETTING. -On a transport type aircraft the fuel tank system is vented through: RAM AIR SC OOPS ON THE UNDERSIDE OF THE WING. the batteries used are mainly Cadmium-Nickel. 6 -On design purpose. -On an aircraft provided with resistance and capacitance variation type fire det ection loops. -On detection of a persistent phase imbalance between an AC generator connected to the main bus bars and other AC generators. the protection device that opens is/are the: TIE B REAKER(S). hence higher power 3. g ood charging and discharging capability at high rating 4. the Krueger flaps are: LEADING EDGE FLAPS CLOSE TO THE WING ROO T -On board present aircraft. 5. This allows: THE CORE TEMPERATURE TO DIMINISH. the electrolyte density re mains unchanged during charging. THE HIGHER THE MAX IMUM COMPRESSION RATIO IS -On detection of a persistent overvoltage fault on an AC generator connected to the aircraft AC busbars. high internal resistance. a gas turbine engine should be run at "GROUN D IDLE" for a short period. -On four-stroke piston engines. the batteries are charged in flight from: A TRANSFORMER RECTIFIER UNIT. wider permissible temperature range 5. Their advantages are: 1. the theoretical valve and ignition settings are readjusted in order to increase the: OVERALL EFFICIENCY -On landing and prior to shut down. good storage capability 6. 4. a fire alarm is initiated by a temperature increase detected: AT ANY ISOLATED POINT OF THE LOOPS OR ELSE GENERALLY ON ALL THE LOOPS -On an airplane. . The combination of correct statement is: 3. the on-board protection device opens: THE EXCITER BREAKER AND THE GENER ATOR BREAKER. low risk of thermal runaway 2. sturdiness owing to its metal casing 7.-On an aeroplane using AC as primary power supply. the relationship between the fuel octane rating and the maxi mum compression ratio of a piston engine is: THE HIGHER THE OCTANE RATING IS. best economy is at the point marked: 1 -On the ground. .2. 3. cockpit windows are protected against icing by: E LECTRIC HEATING. air for air conditioning The combination which regroups al l of the correct statements is: 1. -On-board electrical systems are protected against faults of the following type: 1. -On most transport aircraft. AC generator under-voltage 3.5 -Once the engine has started.-On large aeroplanes equipped with power brakes. over-current 4. the low pressure pumps of the fuel system are: CENT RIFUGAL PUMPS. the low pressure pumps of the fuel system are: CENT RIFUGAL PUMPS. -On most transport aircraft. AC generator over-voltage 2. ignition systems of piston engines are: INDEPENDEN T OF THE ELECTRICAL SYSTEM OF THE AIRCRAFT.4. the main source of power is der ived from: THE AEROPLANE'S HYDRAULIC SYSTEM. hydraulic pressure 4. -On most modern airliners the cabin pressure is controlled by regulating the: AI RFLOW LEAVING THE CABIN. -On modern transport aircraft. undue vibration of AC generators The combination of correct statements is : 1. over-speed 5. the Auxiliary Power Unit (APU) can provide: 1. -On most transport jet aircraft. ai r for starting system 3. unde r-frequency 6. DRIVEN BY AN ELECTRIC MOTOR. the low pressure pumps of the fuel system are s upplied with electric power of the following type: 115 V AC -On the attached diagram showing the power output of a piston engine as a functi on of mixture richness. 2. 4. electricity 2. -One of the advantages of multiple-spool jet engine designs is that: A SMALLER A IR STARTER DRIVING ONLY A SINGLE SPOOL CAN BE USED. -One design method to avoid control surface flutter is: ENSURING CORRECT MASS DISTRIBUTION WITHIN THE CONTROL SURFACE. -One indication of inadequate bonding of aircraft components may be: STATIC NOIS ES CAN BE HEARD ON THE RADIO.-One advantage of having three instead of two spools in some high-bypass turbofa n engine is that: FEWER VARIABLE STATOR VANES AND VARIABLE INLET GUIDE VANES ARE REQUIRED TO PREVENT COMPRESSOR STALL AT LOW ROTOR SPEEDS. -One of the functions of a gas turbine engine subsonic intake is to: DECREASE AI RFLOW VELOCITY. -One of the advantages of a turbocharger is: TO MAKE THE POWER AVAILABLE LESS AFFECTED BY ALTITUDE. -One function of a rib is: TO MAINTAIN THE AERODYNAMIC SHAPE OF THE WING. -One of the advantages of an annular combustion chamber is: A REDUCED THERMAL ST RESS ON THE TURBINE. -One of the functions of an accumulator in a hydraulic system is: TO DAMP PRESSU RE SURGES IN THE SYSTEM. -One of the causes of high oil temperature in a gas turbine engine at constant p ower setting is: MALFUNCTION OF THE HEAT EXCHANGER. . In an em ergency in the case of depressurization. 4. WHILST THAT ACROSS THE EARLY STAGES IS INCREASED. In an emergency in case of smoke or toxic gases in th e cockpit. During a normal flight. -One of the purposes of compressor bleed valves is to: DECREASE THE AIRFLOW ACRO SS THE REAR COMPRESSOR STAGES. 3. -Oxygen systems on pressurized airplanes are used to provide oxygen: 1. In an emergency in the case of the indisposition of a passenger. FLUID TEMPERATURE AND QUANTITY. 2. -One reason to fit a tip shroud to a turbine blade is to: INCREASE TURBINE EFFIC IENCY. -Overcentre mechanisms in landing gear systems are used to: LOCK THE LANDING GEA R IN THE UP AND/OR DOWN POSITIONS.-One of the purpose of the fuel system booster pumps to be submerged in the fuel is: TO FACILITATE THE PRIMING OF THE PUMPS. The combination regrouping all the correct statements is: 1. -Overheating of a piston engine is likely to result from an excessively: WEAK MI XTURE. -One of the purposes of the fuel system booster pumps being submerged in fuel is to: COOL THE PUMPS. .4 -Parameters to monitor a hydraulic system in the cockpit can be: PRESSURE. -One of the purposes of the bleed valves fitted to axial flow compressors is to: REDUCE THE TENDENCY TO COMPRESSOR STALL. -One stage of an axial compressor comprises: A ROW OF ROTOR BLADES FOLLOWED BY A ROW OF STATOR VANES. -Reflection from ionospheric layers is used in the following radio frequencies: HF -Regarding (1) a fuse and (2) a circuit breaker: (1) IS NOT RESETTABLE. to cool the hydraulic fluid. In re spect of the AC generator it can be said that the: EXCITER CONTROL RELAY AND THE GENERATOR BREAK ER OPEN. (2) IS R ESETTABLE. -Power plant fire extinguishers are operated by: AN ELECTRICALLY FIRED CARTRIDGE RUPTURING A SEAL IN THE HEAD OF THE BOTTLE. 4. -Pneumatic mechanical ice protection systems are mainly used for: WINGS. -Prolonged running at low rpm can have an adverse effect on the functioning of t he: SPARK PLUGS. 2. -Purposes of an accumulator in an hydraulic system are: 1. -Pulling the fire shutoff handle causes a number of devices to disconnect.-Pneumatic mechanical devices that provide ice protection: ARE USUALLY USED AS D E-ICING DEVICES. to serve as a limited alternate source of pressure. 3. ELEVATORS AND RUDDER. t o serve as a main pressure source for normal operation. . to damp pressure fluc tuations. -Pre-ignition refers to the condition that may arise when: THE MIXTURE IS IGNITE D BY ABNORMAL CONDITIONS WITHIN THE CYLINDER BEFORE THE SPARK OCCURS AT THE PLUG -Primary flight controls are: AILERONS. 3. The combination that regroups all of the c orrect statements is: 1. The specific fuel consumption increases slightly as the pressure altitude decreases at constant TAS: I IS INCORRECT. The specific fuel consumption decreases slightly as the pressure altitude de creases at constant TAS: I IS INCORRECT. The specific fuel consumption increases slightly as the pressure altitude decreases at constant TAS: I IS CORRECT. The maximum thrust remains constant as the pressure altitude decreases. -Regarding a jet engine: I. II. The specific fuel consumption decreases slightly as the pressure altitude increases at constant TAS: I IS CORRECT. II IS INCORRECT. The specific fuel consumption remains constant as the pressure altitude decr eases at constant TAS: I IS INCORRECT. II IS INCORRECT. -Regarding a jet engine: I. The specific fuel consumption decreases slightly as the pressure altitude in creases at constant TAS: I IS INCORRECT.-Regarding a jet engine: I. at constant TAS: I IS CORRECT. II. The maximum thrust increases as the pressure altitud e decreases. II. -Regarding a jet engine: I. II. II IS CORRECT. -Regarding a jet engine: I. -Regarding a jet engine: I. The maximum thrust increases slightly as the pressur e altitude increases. II IS CORRECT. -Regarding a jet engine: I. -Regarding a jet engine: I. II. at con stant TAS: I IS CORRECT. The maximum thrust decreases as the pressure altitud e increases. II IS CORRECT. II IS INCORRECT. The maximum thrust decreases as the pressure altitud e increases. II. The maximum thrust remains constant as the pressure altitude decreases. The maximum thrust increases as the pressure altitud e decreases. II. . The specific fuel consumption is inversely proportional to pressure altitude. The specific fuel consumption is proportional to pressure altitude. II. The maximum thrust decreases slightly as the pressur e altitude decreases. II IS INCORRECT. II IS CORRECT. Ion detectors are used to detect: SMOKE. -Regarding the oxygen system of a JAR 25 aeroplane: WITH THE SETTING ON "NORMAL" . the correct statement is: AERODYNAM IC PERFORMANCES OF THE WINGS ARE MAINTAINED AND THERE IS A REDUCTION OF MAXIMUM ENGINE THRUST. -Regarding a jet engine: I. II IS INCORRECT. -Regarding Ohm's law: THE CURRENT IN A CIRCUIT IS DIRECTLY PROPORTIONAL TO VOLTAGE. II IS INCORRECT. . The specific fuel consumption remains constant as the pressure altitude incr eases at constant TAS: I IS INCORRECT. -Severe compressor stall can be indicated amongst others by: A RISE IN TURBINE G AS TEMPERATURE (TGT) AND A CHANGE IN VIBRATION LEVEL. the pass enger must: FIRMLY PULL THE MASK TOWARDS HIS FACE. THE CREW BREATHES A MIXTURE OF OXYGEN AND CABIN AIR. II. to enable the oxygen to flow. -Ruddertrim adjustment in an aeroplane with irreversible flight controls is: AN ADJUSTMENT OF THE ZERO FORCE RUDDER POSITION. The maximum thrust remains constant as the pressure altitude increases. II. -Regarding a thermal wing anti-icing system. The specific fuel consumption increases slightly as the pressure altitude in creases at constant TAS: I IS INCORRECT.-Regarding a jet engine: I. -Regarding the chemical oxygen generator. -Rotor brake discs are manufactured from: STEEL OR CARBON FIBRE. -Regarding fire detection. The maximum thrust remains constant as the pressure altitude increases. . the wheels tend to describe a sinusoidal motion on the ground 2. an accumulator associated with the s teering cylinder. -Spark plug fouling is more likely to happen if: THE AIRCRAFT DESCENDS CONTINUOU SLY AT IDLE POWER. 4. the wheels no longer respond to the pilot's actions.-Severe compressor stall can be observed amongst others by: A RISE IN TURBINE GA S TEMPERATURE (TGT) AND A INCREASE IN VIBRATION LEVEL. -Skip distance is the: RANGE FROM THE TRANSMITTER TO THE FIRST SKY WAVE -Smoke detector systems are installed in the: UPPER CARGO COMPARTMENTS (CLASS E) . the torque link 4. -Should a hydraulic pump seize during operation: THE QUILL DRIVE WILL SHEAR TO O FFLOAD AND PROTECT THE GEARBOX. -Smoke detectors fitted on transport aircraft are of the following type: OPTICAL OR IONIZATION -Some gas turbine engines have multiple stages in the HP and LP turbines: BECAUS E ONE STAGE DOES NOT GENERATE SUFFICIENT SHAFT POWER. -Shuttle valves will automatically: SWITCH HYDRAULICALLY OPERATED UNITS TO THE M OST APPROPRIATE PRESSURE SUPPLY. -Shimmy occurs on the nose wheel landing gear during taxiing when: 1. -Significant torsion effects in a wing during flight can be caused by: AILERON D EFLECTION. The combination of correct statements is: 1. This effect is overcome by means of: 3. -The accumulator in a hydraulic system works as: AN ENERGY STORAGE. -Static dischargers: 1. hydraulic pumps 5. THE MORE THE SPARK IS ADVANCED -Specific fuel consumption for a turbo-prop engine can be expressed in kg per: H OUR PER UNIT OF SHAFT POWER. are placed on wing and tail tips to facilitate electrical discharge. -Specific fuel consumption is defined as the: MASS OF FUEL REQUIRED TO PRODUCE U NIT POWER FOR UNIT TIME. 5. are used to reset the electrostatic potential of the aircraft to a value approximating 0 volts. high pressure fuel pumps The combination regrouping all the correct sta tements is: 2. -The advantages of a chemical oxygen source for the passenger cabin are : 1. -Static gas temperature decrease when flowing at a subsonic speed through a jet engine exhaust nozzle because the: exhaust nozzle is convergent.5. AC generator through its constant speed drive (CSD) 3. 4.4. oil p umps 4. -The "cabin differential pressure" is: CABIN PRESSURE MINUS AMBIENT PRESSURE.-Spark timing is related to engine speed in the way that the: FASTER THE ENGINE FUNCTIONS. limit the risks of transfer of electrical charges between the aircraft and the electrified clouds. thrust reverser pneumatic motors 2. -The ABS (Auto Brake System) is being disconnected after landing: BY PILOT ACTIO N -The accessory units driven by the accessory gearbox of a turbo-jet engine are t he: 1. are located on wi ng and tail tips to reduce intererence with the on-board radiocommunication systems to a minimum. 5. 2. are used to set all the parts of the airframe to the sam e electrical potential. red uced weight and . 4. 3. The combi nation regrouping all the correct statements is : 2. 3. volume. higher internal resistance. no risk of expl osion. greater autonomy. 2. hence higher power 3. -The advantages of a gaseous oxygen source for the passenger cabin are : 1. but the absolute exit velocity is higher than the absolute entry velocity of the rotor. high starting torque 3. easy storage and maintenance . The combination regrouping all the correct statements is : 1. possibility to regulate flow. easy to convert i nto direct current 6. 4. 6 -The advantages of a gaseous oxygen source compared with a chemical source for t he passenger cabin are: 1. Increase of short-circuit risk 4. Easy fault detection 3. 3. 4. 5 -The advantages of alternating current on board an aircraft are: 1. flexibility in use 4. a gr eater autonomy. no risk of explosion. 5. 5. Circuits are not single-wired lines The combination regrouping all the correct statements is : 1. 6 -The advantages of fly-by-wire control are: 1. The combination that regroups all of the correct statements is: 2. 4. Reduction of short-circuit risk 5. 3. -The air flow passages between adjacent axial compressor rotor blades are diverg ent. immunity to different interfering signals 5 . 3. improvement of piloting quality throughout the flight envelope The combination regrouping all the correc t statements is: 3 and 5 -The advantages of grounding the negative pole of the aircraft structure are: 1. This is because: PART OF THE COMPRESSOR WORK DELIVERED TO THE AIR IS CONVERTED INTO KINETIC ENERGY. easy maintenance of machines The combination of correct statements is: 3. lesser sensitivity to lightning strike 3. The combination regrouping all the correct state ments is: 1. reduction of the electric and hyd raulic power required to operate the control surfaces 2. simple conne ction 2. low er risk of thermal runaway 2. 6. 2. 2. 4 -The advantages of Nickel -Cadmium compared with lead-acid batteries are: 1. 3. more capacity. lighter weight of equipment 5. possibility to regulate flow. easy storage and maintenance. constant output voltage The combination which regroups all the correct statements is: 3. direct and indirect weight saving through simplification of systems 4. 4. 2. reversible functioning. . no risk of fire and/or explosion. 2. Weight saving 2. 4. 5. 3. reversible functioning. no maintenance. reduced charging ti me 4. -The aircraft hydraulic system is designed to produce: HIGH PRESSURE AND LARGE F LOW. when connected. -The application of carburettor heating reduces the: DENSITY OF AIR ENTERING THE CARBURETTOR. -The alternators. -The automatic ground spoiler extension system is normally activated during land ing by: MAIN WHEEL SPIN UP. -The axial compressor of a gas turbine engine usually has more stages than its d riving turbine because: THE POWER OUTPUT OF A TURBINE STAGE IS HIGHER THAN THE POWER CONSUMPTION OF A COMPRESSOR STAGE. -The auxiliary power unit (APU) has its own AC generator that: SUPPLIES THE AIRC RAFT WITH THREE-PHASE 115-200 V. . 400 HZ AC.-The air in a piston engine turbo-supercharger centrifugal compressor : ENTERS T HE EYE OF THE IMPELLER AND LEAVES AT A TANGENT TO THE PERIPHERY. -The Automatic Direction Finder uses the following wavelengths: HECTOMETRIC OR K ILOMETRIC. -The automatic fuelling shut off valve: STOPS FUELLING AS SOON AS A CERTAIN FUEL LEVEL IS REACHED INSIDE THE TANK. -The auto-brake system is disconnected during landing: BY PILOT ACTION. are usually connected: IN PARALLEL MODE -The anti-icing method for the wings of large jet transport aeroplanes most comm only used in flight is: THERMAL (USE OF HOT AIR). THUS ENRICHING THE MIXTURE. 3. is the ratio of bypass air mass flow to HP compressor mass flow. 2. The combi nation containing all of the correct statements is: 2 and 4 only. wing root fairing. -The by-pass air in a by-pass type gas turbine engine promotes lower specific fu el consumption by causing an overall: DECREASE IN EXHAUST GAS FLOW AVERAGE VELOCITY AND HIGHER PROPULSIVE EFFICIENCY.are arrange d in series.are arranged in parallel. 3 .open during a fire. 4. -The blade angle of a propeller is the angle between the: REFERENCE CHORD LINE A ND THE PROPELLER PLANE OF ROTATION. The combination that regro ups all of the correct statements is: 1. 2 . -The blades in an axial flow compressor decrease in size from the: LOW PRESSURE TO THE HIGH PRESSURE STAGES IN AN ATTEMPT TO SUSTAIN AXIAL VELOCITY. 4. can be determined from the inlet air volume flow and the HP compressor volume flow: I I S CORRECT. II IS INCORRECT. upper skin surface. -The built-in passenger oxygen system be activated by: SWITCHING THE PASSENGER O XYGEN ON. II.-The bending loads on a cantilever wing due to lift are carried by the: 1. lower skin surface. . 2. spar or spars. -The bypass ratio: I. -The by-pass air in a turbo fan engine has the effect of a lower specific fuel c onsumption by causing an overall: DECREASE IN AVERAGE EXHAUST GAS FLOW VELOCITY AND A HIGHER MASS FLOW. 4 .close during a fire. -The blade angle of a constant-speed propeller: INCREASES WITH INCREASING TRUE A IR SPEED. -The bimetal strip detectors of an engine fire detection system: 1 . can be determined from the inlet air volume flow and the HP compressor volume flow: I I S INCORRECT. II IS CORRE CT. can be determined from the bypass air mass flow and the HP compressor mass flow: I IS INCORRECT. II. is the ratio of inlet air mass flow to exhaust air mass fl ow. -The capacitance type fuel gauging system indicates the fuel quantity by measuri ng the: DIELECTRIC CHANGE BETWEEN FUEL AND AIR.-The bypass ratio: I. c an be determined from the inlet air mass flow and the HP compressor mass flow: I IS INCORRECT. can be determined from the inlet air mass flow and the HP compressor mass flow: I IS CO RRECT. -The cabin pressure is regulated by the: OUTFLOW VALVE. -The capacity of a battery is the: AMOUNT OF AMPERE HOURS THAT A FULLY CHARGED BATTERY CAN SUPPLY. can be determined from the inlet air mass flow and the bypass ma ss flow: I IS INCORRECT. -The bypass ratio: I. II IS CORRECT. is the ratio of the volume of air passing through the inle t to that through the HP compressor. -The bypass ratio: I. I I IS CORRECT. -The bypass ratio: I. II. -The cabin rate of descent is: A CABIN PRESSURE INCREASE. II. II IS CORRECT. -The bypass ratio: I. . II. II. is the ratio of inlet airflow to HP compressor flow. is the ratio of inlet air mass flow to HP compressor mass flow. -The capacity of a battery is given in: AMPERE HOURS. II IS INCORRECT. is the ratio of bypass air mass flow to HP compressor mass flow. a low pressure ratio by sta ge. -The component that converts hydraulic pressure into linear motion is called: AN ACTUATOR OR JACK. 3 . 3 .3 -The characteristics of a centrifugal compressor are: 1 .a low pressure ratio by stage.a high pressure ratio by stage. -The compression ratio of a piston engine is the ratio of the: VOLUME OF THE CYL INDER WITH THE PISTON AT BOTTOM DEAD CENTRE TO THAT WITH THE PISTON AT TOP DEAD CENTRE. -The characteristics of an axial compressor are: 1 . -The chemical oxygen generator supplies oxygen for about: 15 MINUTES. 2 . . 2 .2. The combinati on containing all of the correct statements is: 1 AND 2 ONLY. -The colour of a fresh synthetic hydraulic fluids is: PURPLE. 4 .-The capacity of an accumulator is: THE QUANTITY OF ELECTRICITY THAT THE BATTERY CAN SUPPLY DURING DISCHARGE. 4 .a high pressure ratio by stage.the possibility of compressing a large mass airflow. an Arithmetic and Logic Unit (ALU) 2. -The compressor blades in a rotating gas turbine engine are held in position by: THE MOUNTINGS AND THE RESULTANT OF AERODYNAMIC AND CENTRIFUGAL FORCES. a control and timing unit 3.the inability of compressing a large mass airflow. -The Central Processing Unit (CPU) of a computer essentially consists of: 1.a small diameter.a large diameter. registers The combination which regro ups all the correct statements is: 1. The combination that regroups all of the correct statement s is: 1 AND 3 ONLY. 4 .turbine temperature The combination which regroups all of the correct statements is : 1 . -The compressor surge effect during acceleration is prevented by the: FUEL CONTR OL UNIT (F.propeller RPM 5 .C. -The conditions to be met to activate a shunt generator are: 1. -The conditions most likely to produce the highest engine power are: COLD AND DR Y AIR AT HIGH PRESSURE.pressure .U.). .-The compressor pressure ratio of an axial flow compressor is primarily determin ed by the: NUMBER OF STAGES. 12 VOLT/ 80 AMP HOURS -The contents of an oxygen bottle can be ensure by the: 1 .weight.5 6 -The correct formula to calculate the total displacement of a multi-cylinder pis ton engine is the: PISTON AREA X PISTON STROKE X NUMBER OF CYLINDERS -The correct order of decreasing freezing points of the three mentioned fuels is : JET A.turbine temperature 3 . will create a unit with the following characteristics. -The control of free turbine engines on turboprops. The combination containing all of the correct statements is: 1 AND 2 ONLY. 2 .level.turbine RPM . minimum rota tion speed The combination of correct statements is: 1. presence of a pe rmanent field 2.volume.torque 6 . JET A-1. 3 .a fu el control lever used to select: 4 .a prop eller control lever used to select: 1 . closed electrical circuit 3. generator terminals short-circuited 4. is accomplished by: . 4 -The conditions which can cause detonation are: HIGH MANIFOLD PRESSURE AND LOW REVOLUTIONS PER MINUTE. -The connection in parallel of two 12 volt/40 amp hours batteries.propeller RPM 2 . dump the unusable fuel. 2. 3.JET B -The correct statement about rain protection for cockpit windshields is that: RA IN REPELLENT SHOULD NEVER BE SPRAYED ONTO THE WINDSHIELD UNLESS THE RAINFALL IS VERY HEAVY. 3. -The cylinder head and oil temperature gauges are to exceed the normal operating ranges if a pilot: USES FUEL THAT HAS A RATING LOWER-THAN-SPECIFIED FOR THE ENGINE -The cylinder head and oil temperatures may exceed their normal operating ranges if: A LOWER OCTANE RATING THAN SPECIFIED FOR THE ENGINE IS USED. -The crank assembly of a piston engine comprises the: CRANKSHAFT. -The cylinder head and oil temperatures may exceed their normal operating ranges if: A LOWER OCTANE RATING THAN SPECIFIED FOR THE ENGINE IS USED. adjust fuel distribution 4. feed any engine from any fuel tan k. -The crash/fire axe is part of the safety equipment fitted to passenger aircraft . . to transfer fuel from one tank to another located in the same wing The combination that regroups all of the correct statements is: 1. -The damping element in a landing gear shock absorber used on large aircrafts is : OIL. -The cross-feed fuel system enables: THE SUPPLY OF ANY JET ENGINE FROM ANY FUEL TANK. -The cross-feed fuel system can be used to: 1. Its function is to : OBTAIN FORCED ACCESS TO A FIRE BEHIND A PANEL AND A GENERAL PURPOSE TOOL DURING EVACUATION. CONNECTING ROD S AND PISTONS. -The diffuser in a centrifugal compressor is a device in which the: PRESSURE RIS ES AND VELOCITY FALLS. 5 -The disadvantages of axial flow compressors compared to centrifugal flow compre ssors are: 1 more expensive to manufacture 2 . -The effect of ram air on the operation of a gas turbine engine is: AN INCREASE IN THE EFFICIENCY OF THE ENGINE.lower airflow 3 . poor autonomy. 5. 3. -The demand valve of a diluter-demand type oxygen regulator in normal mode.greater vulnerability to foreign object damage 4 lower pressure ratio The combination which regroups all of the correct answers is: 1 3 -The Distance Measuring Equipment (DME) uses the following wavelengths: DECIMETR IC. The combination regrouping all the correct statements is: 1.-The de-icing system which is mostly used for the wings of modern turboprop aero planes is: PNEUMATIC BOOTS. 2. -The disadvantages of a chemical oxygen source for the passenger cabin are : 1. -The diagram shown in annex represents a jet fuel system. a heavy and bulky system. -The electronic engine control of a FADEC gas turbine engine checks: ALL INPUT A ND OUTPUT DATA. -The elements specifically protected against icing on transport aircraft are: 1) engine air intake and . oper ates when the: USER BREATHES IN. non reversible functioning. ris ks of explosion. The fuel-flow measurem ent is carried out : AFTER HIGH PRESSURE VALVE (ITEM 4). a flow which cannot be modulated. 4. 3. 2. -The FADEC of a gas turbine engine normally includes: AN ENGINE OVERSPEED AND/OR AN EGT PROTECTION FUNCTION. 4. ELECTRICAL WIRING. -The expression "secondary flight control" applies to the: 1: elevator 2: speed brake 3: lift-augmentation devices 4: roll spoiler The combination that regroups all of t he correct statements is: 2. -The expression "primary flight control" applies to the: 1: elevator. -The expression "primary flight control" applies to the: 1: stabiliser 2: rudder 3: speed brake 4: aileron The combination that regroups all of the correct statements is: 2. 6) cabin windows. -The expression "secondary flight control" applies to the: 1: stabiliser 2: rudd er 3: speed brake 4: aileron The combination that regroups all of the correct statements is: 1. 4: roll spoiler.pod. 4) pitot tubes and waste water exhaust ma sts. 3) radome. 4. -The essential difference between aircraft AC alternators and DC generators (dyn amos) is that the: INDUCED (OUTPUT) WINDINGS OF THE ALTERNATORS ARE FIXED (STATOR). AND THE DYNAMOS HAVE A FIXED INDUCTOR (FIELD) COIL. -The FADEC of a gas turbine engine consists of: AN ELECTRONIC ENGINE CONTROL UNI T AND ITS PERIPHERALS (FUEL METERING. 3. 3: lift-augmentation devices. The combination regrouping all the correct statements is : 1. 5) leading edge of wing. SENSORS ). 4. 5 -The equipment of an oxygen supply installation must be kept absolutely free of oil or grease traces as: THESE SUBSTANCES CATCH FIRE SPONTANEOUSLY IN THE PRESENCE OF OXYGEN UNDER PRESSURE. The combination that regroups all of the correct state ments is: 1. 3. 8) electronic equipment co mpartment. 2: speed b rake. 7) trailing edge of wings. . 2) front glass shield. ACTUATORS. is the: FLASH POINT .-The fan in a high by-pass ratio turbo-jet engine produces: THE GREATER PART OF THE THRUST. -The first indication of carburettor icing. -The fan of a turbo-fan engine is driven by: THE LP TURBINE. -The fuel cross-feed system: ALLOWS FEEDING OF ANY ENGINE FROM ANY FUEL TANK. the vapour ignites i n contact with a flame and extinguishes immediately. -The frequency of the current provided by an alternator depends on: ITS ROTATION SPEED -The fuel cross-feed system enables: THE SUPPLY OF ANY ENGINE FROM ANY FUEL TANK . -The fuel supply system on a jet engine includes a fuel heating device. in aeroplanes equipped with constant speed propellers. AT LOW FUEL TEMPERATURE. ALTHOUGH N2 MAY ACCELERATE NORMALLY. under standard conditions. upstream of the main fuel filter so as to: PREVENT. -The frequency of an AC generator is dependent on the: NUMBER OF PAIRS OF POLES AND THE SPEED OF THE MOVING PART. at which. THE RISK OF ICE FORMATION FROM WATER CONTAINED IN THE FUEL. -The fuel tanks of aircrafts must be checked for wáter: BEFORE THE FIRST FLIGHT OF THE DAY OR AFTER A LONG TURNAROUND TIME -The fuel temperature. -The following problems may occur when starting a twin-spool turbofan engine: NO N1 ROTATION. during cruise would most likely be a: DECREASE IN MANIFOLD PRESSURE. -The function of a NOT logic gate within a circuit is to: INVERT THE INPUT SIGNA L SUCH THAT THE OUTPUT IS ALWAYS OF THE OPPOSITE STATE. -The function of a CSD in an AC generating system is to: DRIVE THE GENERATOR AT A CONSTANT SPEED. -The function of a vibrator in some gas turbine ignition systems is to provide: A DC CURRENT TO THE TRANSFORMER TO FACILATE THE GENERATION OF A HIGHER VOLTAGE TO THE IGNITION -The function of an accumulator in a hydraulic brake system is: TO SUPPLY A LIMI TED AMOUNT OF BRAKE ENERGY IN THE EVENT OF FAILURE OF THE HYDRAULIC SYSTEM NORMALLY .-The fuel-oil heat exchanger: COOLS THE OIL AND HEATS THE FUEL. -The function of a constant speed drive (CSD) is to ensure: THAT THE GENERATOR P RODUCES A CONSTANT FREQUENCY. -The function of a scissor (torsion link) in a landing gear is to: PREVENT ANY R OTATION OF THE OLEO STRUT IN THE LANDING GEAR SHOCK ABSORBER. -The function of a hydraulic selector valve is to: DIRECT SYSTEM PRESSURE TO EIT HER SIDE OF THE PISTON OF AN ACTUATOR. -The function of a feed box in the fuel tank is to: INCREASE THE FUEL LEVEL AT T HE BOOST PUMP LOCATION -The function of a fusible plug is to: PROTECT THE TYRE AGAINST EXPLOSION DUE TO EXCESSIVE TEMPERATURE. 3. -The function of the rudder limiter system is: TO RESTRICT RUDDER DEFLECTION DUR ING FLIGHT AT HIGH IAS. increase air p ressure at the fuel nozzles. -The fuselage structure of a pressurised transport aeroplane is an example of a: SEMI-MONOCOQUE STRUCTURE. -The gas turbine illustrated is of the following type: FREE TURBINE AND CENTRIFU GAL COMPRESSOR -The greatest risk created by a free turbine overspeed is: BURSTING OF THE FREE TURBINE DISK. reduce the average axial flow speed in order to stabilise the flame front. 3. -The function of the Generator Breaker is to close when the voltage of the: GENE RATOR IS GREATER THAN BATTERY VOLTAGE AND TO OPEN WHEN THE OPPOSITE IS TRUE -The function of the primer pump in a reciprocating engine is to: PROVIDE ADDITI ONAL FUEL FOR AN ENGINE START.SUPPLYING THE BRAKES. -The function of the swirl vanes round the fuel nozzles is to: 1. The combination th at regroups all of the correct statements is: 2. generate a swirl of incoming air to enhance mixing of the fuel with air. -The function of ribs in a wing is to: GIVE THE WING THE DESIRED AERODYNAMIC SHA PE. . -The functions of an LP booster pump in a gas turbine fuel system are to: AVOID VAPOUR LOCKING AND PREVENT CAVITATION OF THE HP FUEL PUMP. 2. -The high Altitude Radio Altimeter uses the following wavelengths: DECIMETRIC. -The ice protection system currently used for the most modern jet aeroplanes is the: HOT AIR SYSTEM. -The hydraulic device. -The ignition system of a running piston engine receives electrical energy from: ROTATING PERMANENT MAGNETS. -The illumination of the green landing gear light indicates that the landing gea r is: LOCKED-DOWN. is a: CHECK VALVE. -The ignition system generally used for small aircrafts is a: HIGH TENSION SYSTE M.-The heat for the anti-icing system of a turbofan engine intake is provided by: BLEED AIR FROM THE HP COMPRESSOR. -The hydraulic systems which works correctly is shown in the figure: B -The ice protection for propellers of modern turboprop aeroplanes works: ELECTRI CALLY. . -The heating facility for the windshield of an aircraft is: USED ON A CONTINUAL BASIS AS IT REDUCES THE THERMAL GRADIENTS WHICH ADVERSELY AFFECT THE USEFUL LIFE OF THE COMPONENTS. -The highest load on the torsion link in a bogie gear is: WHILST TURNING ON THE GROUND WITH A SMALL RADIUS. which functionality is comparable to an electronic diode. -The internal geometry of a turbofan intake for a subsonic commercial aeroplane is: DIVERGENT IN ORDER TO REDUCE AIRFLOW VELOCITY AND INCREASE STATIC PRESSURE IN FRONT OF THE FAN. -The level in a hydraulic reservoir will: FLUCTUATE WITH ACCUMULATOR PRESSURE. no crew action is required 3 .-The inner surface of a heated windscreen is of: SOFT POLYCARBONATE. -The input and output of a static inverter are respectively: DC AND AC.in case of accidental drop of the "continuous flow" pas senger masks.the sm oking ban is imperative when used 2 . .the system's filling adaptors must be greased with non-freezing or graphite grease The combin ation which regroups all of the correct statements is: 1 3 -The Instrument Landing System (ILS) uses the following wavelengths: METRIC. -The installation and use of on-board oxygen generators is such that: 1 . -The kind of compressor normally used as a supercharger is: A RADIAL COMPRESSOR. -The lubricating system of an air cooled piston engine is used to: REDUCE INTERN AL FRICTION AND PROVIDE COOLING. -The lubricating system of an aircraft engine is used to: AID IN DISSIPATION OF HEAT -The main advantage of a constant speed propeller as compared to a fixed pitch p ropeller is a: HIGH EFFICIENCY IN A MUCH WIDER SPEED RANGE OF THE AEROPLANE.no trace of grease must be found in the system assem bly 4 . -The logic symbol shown represents (assuming positive logic) : AN INVERT OR NOT GATE. -The mechanism to change the propeller blade angle of a small piston engine aero plane in flight is operated: HYDRAULICALLY BY ENGINE OIL. -The maximum cabin differential pressure of a pressurised aeroplane operating at FL370 is approximately: 9. -The main function of an air cycle machine is to: COOL THE BLEED AIR. -The main purpose of a turbocharger is to: MAINTAIN POWER WITH INCREASING ALTITU DE. -The mixture control for a carburettor achieves its control by: VARYING THE FUEL SUPPLY TO THE MAIN DISCHARGE TUBE.0 PSI -The measured output power components of a constant frequency AC system are: KVA AND KVAR.-The main feature of BCF fire extinguishers is that they: ACT AS FLAME INHIBITOR S BY ABSORBING THE AIR'S OXYGEN. -The main purpose of a Constant Speed Drive unit is to: MAINTAIN A CONSTANT FREQ UENCY. -The minimum airborne equipment required for operation of a the VHF direction fi nder is a: VHF TRANSMITTER-RECEIVER OPERATING IN THE 118 MHZ TO 136 MHZ RANGE. -The mixture controller of a carburettor: VARIES THE FUEL SUPPLY TO THE MAIN DIS CHARGE . -The main purpose of the mixture control is to: ADJUST THE FUEL FLOW TO OBTAIN T HE CORRECT FUEL/AIR RATIO. -The moving part in an AC generator is usually referred to as the: rotor -The number of hand fire extinguishers which have to be installed in the passeng er cabin according to JAR-OPS depends on the number of : SEATS IN THE CABIN. -The most widely used electrical frequency in aircraft is: 400 HZ. -The most unfavourable conditions for adequate inlet air flow of a turbofan engi ne are: MAXIMUM TAKE-OFF THRUST. 4. 2. -The most common extinguishing agent used in gas turbine engine fire protection systems is: HALON. idle wheel speed (measured) 2.NOZZLE. -The octane rating of a fuel characterises the : THE ANTI-KNOCK CAPABILITY . -The modern anti-skid processes are based on the use of a computer whose input d ata is: 1. ZERO FORWARD SPEED AND STRONG CROSSWIND CONDITIONS.C STARTER/G ENERATOR. desired idle wheel train slipping rate 5. tire pressure The combination regroupi ng all the correct statements is : 1. -The most common type of starter used on a helicopter engine is: A D. -The most important oil system instrument indication during gas turbine engine s tart is: OIL PRESSURE. brake temperature (me asured) 4. braked wheel speed (measured) 3. -The most common material used in the construction of gearbox casings is: MAGNES IUM ALLOY. -The part of a piston engine that transforms reciprocating movement into rotary motion is termed the: CRANKSHAFT . pneumatic for the gaseous oxygen system. -The opening of the doors giving access to the oxygen masks for the passengers i s: 1. 3. WHICH IS DISTRIBUTED TO THE SPARK PLUGS. -The oil system for a piston engine incorporates an oil cooler that is fitted : IN THE RETURN LINE TO THE OIL TANK AFTER THE OIL HAS PASSED THROUGH THE SCAVENGE PUMP -The oil system of a gas turbine engine may be fitted with magnetic plugs. 2 -The operating principle of float-type carburettors is based on the: DIFFERENCE IN AIR PRESSURE AT THE VENTURI THROAT AND THE AIR INLET -The operating principle of magnetos in a piston engine ignition system consists of: BREAKING THE PRIMARY CIRCUIT IN ORDER TO INDUCE A LOW AMPERAGE. The combina tion regrouping all the correct statements is: 1. electrical for the chemical oxygen system. 4. -The oil supply to gas turbine engine bearings is maintained in the event of the main oil filter becoming clogged by: DIFFERENTIAL PRESSURE OPENING THE BYPASS VALVE OF THE MAIN OIL FILTER. that: PROVIDE WARNING OF IMPENDING FAILURE WITHOUT HAVING TO REMOVE THE FILTERS FOR INSPECTION.-The octane rating of a fuel characterises the: RESISTANCE TO DETONATION. or ch ip detectors. pneu matic for the chemical oxygen system. -The pack cooling fan provides: COOLING AIR TO THE PRIMARY AND SECONDARY HEAT EXCHANGER DURING SLOW FLIGHT AND GROUND OPERATION. electrical for the gaseous oxygen system. HIGH VOLTAGE CURRENT. 2. -The power output of a piston engine without supercharging increases with increa sing altitude in standard atmosphere at constant Manifold Air Pressure (MAP) and RPM because of t he: INCREASE OF THE AIR DENSITY BEHIND THE THROTTLE VALVE. -The pressure usually produced by the booster pumps of the fuel supply system of a large jet transport aeroplane is within the following range: 20 TO 50 PSI -The pressurisation load on the skin of a fuselage is: TENSION. -The phase relationship between two unparalleled AC generators: IS UNIMPORTANT.-The passenger oxygen mask will supply: A MIXTURE OF CABIN AIR AND OXYGEN. is: B RAKE HORSE POWER. which will be measured by a friction brake. -The power of a piston engine. -The power required for field excitation of the main rotor in modern constant-fr equency alternators is directly controlled by: THE VOLTAGE REGULATOR. -The power output of a diesel engine without a turbo charger is regulated by: FU EL FLOW ONLY . . -The power of a piston engine decreases during a climb with a constant power lev er setting because of the decreasing: AIR DENSITY. -The power output of a piston engine can be calculated by: TORQUE TIMES RPM. -The power output of a generator is controlled by: VARYING THE FIELD STRENGTH. -The primary performance indicator (cockpit instrument) for the thrust of a turb ofan engine is: EITHER EPR OR N1. -The pressurization of fuel tanks is maintained by: THE FUEL VENT SYSTEM. -The primary reason for a limitation being imposed on the temperature of gas flo w in a gas turbine is to: ENSURE THAT THE MAXIMUM ACCEPTABLE TEMPERATURE AT THE TURBINE BLADES IS NOT EXCEEDED. of a gas turbine engine is to: DECREASE THE FLOW VELOCITY. THRUST LEVER ANGLE. -The primary function of the diffuser. FUEL SHUT-OFF. located between the compressor and the co mbustion chamber. -The primary reason for venting an engine oil tank is to: PREVENT EXCESSIVE PRES SURE IN THE TANK. -The primary input signals for a hydro-mechanical gas turbine engine fuel contro l system include: N2.-The pressurisation system of an aeroplane: HAS THE CAPABILITY TO MAINTAIN A CAB IN PRESSURE HIGHER THAN AMBIENT PRESSURE. -The primary reason for a limitation being imposed on the temperature of the gas flow is to: ENSURE THAT THE MAXIMUM ACCEPTABLE TEMPERATURE AT THE TURBINE BLADES IS NOT EXCEEDED. -The pressurising function of the pressurising and dump valve in a gas turbine e ngine fuel system is: TO ADMIT FUEL TO THE NOZZLES ONLY IF THE FUEL PRESSURE IS HIGH ENOUGH FOR SUFFICIENT ATOMISATION. COMPRESSOR DISCHARGE PRESSURE. COMPRESSOR INLET TEMPERATURE. . . -The principle of damage tolerance in structural design of an aircraft is based on the: CAPABILITY TO WITHSTAND A CERTAIN AMOUNT OF WEAKENING OF THE STRUCTURE WITHOUT CATASTROPHIC FAILURE. -The purpose of a diluter demand regulator in an oxygen system is to : DELIVER O XYGEN FLOW WHEN INHALING.when there is a battery overheat condition 3 .in case of an internal short circuit 4 . -The purpose of a compressor bleed valve is to prevent surging: AT LOW COMPRESSO R RPM.in case of a fault on the ground power unit The combi nation which regroups all of the correct statements is: 1 . -The principle of fail safe design of an aircraft is based on the: REDUNDANCY OF THE STRUCTURE OR EQUIPMENT.-The principle of aeroplane propulsion is to generate a propelling force by: ACC ELERATING AIR OR GAS IN ORDER TO OBTAIN A REACTION FORCE. -The principle of on condition maintenance is based on the: MONITORING OF CRITIC AL PARAMETERS AND THE REPLACEMENT OF PARTS IF A LIMIT VALUE IS EXCEEDED -The principle of the safe life design of an aircraft is based on the: REPLACEME NT OF PARTS AFTER A GIVEN NUMBER OF CYCLES OR HOURS OF USE. -The purpose of a distributor in an ignition system is to distribute: SECONDARY CURRENT TO THE SPARKING PLUGS.2 -3 -The purpose of a chip detector in the oil system of an engine/gearbox is to ind icate that: THERE ARE METAL PARTICLES IN THE OIL. -The purpose of a battery control unit is generally to isolate the battery: 1 from the bus when the battery charge has been completed 2 . 4 . 2 .provide a for electrical devices. -The purpose of an accumulator in an hydraulic system is to: STORE ENERGY. . -The purpose of baffle check valves fitted in aircraft fuel tanks is to: PREVENT FUEL MOVEMENT TO THE WING TIP.isolate all components electrically.ensure zero voltage tween aircraft components. -The purpose of cabin air flow control valves in a pressurization system is to: MAINTAIN A CONSTANT AND SUFFICIENT MASS AIR FLOW TO VENTILATE THE CABIN AND MINIMISE . -The purpose of an accumulator in a hydraulic system is: TO DAMP THE FLUID PRESS URE VARIATIONS. -The purpose of bonding the metallic parts of an aircraft is to: 1 ctrolytic corrosion between mating surfaces of similar metals. -The purpose of a variable bypass valve. -The purpose of bonding the metallic parts of an aircraft is to : PROVIDE SAFE D ISTRIBUTION OF ELECTRICAL CHARGES AND CURRENTS. 3 . -The purpose of baffles in an aeroplane's integral fuel tank is to: RESTRICT THE FUEL MOVEMENTS IN THE TANK. -The purpose of a voltage regulator is to control the output voltage of the: GEN ERATOR AT VARYING LOADS AND SPEEDS.prevent ele difference be single earth 4. fitted between the LP and HP compressor of an axial flow compressor.-The purpose of a trim tab (device) is to: REDUCE OR TO CANCEL CONTROL FORCES. The combination that regroups all of the correct statements is: 2. is to: PREVENT STALL IN THE LP COMPRESSOR. control of cabin altitude rate-of-ch ange. is to: ASSIST THE SKIN WITHSTAND LONGITUDINAL COMPRESSIVE LOADS. balancing aircraft altitude with cabin altitude 5. -The purpose of stringers. used in fuselage construction. . 3. control of cabin altitude. 2. -The purpose of gas turbine engine trending is: TO ENHANCE MAINTENANCE PLANNING AND DETECT ANOMALIES. keeping a constant differential pressure throughout all the flight phases.CABIN PRESSURE SURGES. 2. -The purpose of the cabin pressure controller. cabi n ventilation 6. -The purpose of static wick dischargers is to: DISSIPATE STATIC CHARGE OF THE AI RCRAFT IN FLIGHT THUS AVOIDING RADIO INTERFERENCE AS A RESULT OF STATIC ELECTRICITY. is to perf orm the following functions: 1. 3 -The purpose of the contact breaker is to: CONTROL THE PRIMARY CIRCUIT OF THE MA GNETO -The purpose of the floor proximity emergency escape path marking system is to: GIVE ADDITIONAL GUIDANCE DURING AN EMERGENCY EVACUATION WITH A REDUCED CABIN VISIBILITY. -The purpose of the blow-in-doors at the air inlets is to: PROVIDE THE ENGINE WI TH ADDITIONAL AIR AT HIGH POWER SETTINGS AND LOW AIR SPEEDS. in the automatic mode. The combination regrouping all the correct statements is : 1. limitation of differential pressure 4. -The purpose of the "Pressure Relief Valve" in a high pressure oxygen system is to: RELIEVE OVERPRESSURE IF THE PRESSURE REDUCING VALVE MALFUNCTIONS -The purpose of the barometric correction in a fuel controller is to: MAINTAIN T HE CORRECT FUEL TO AIR MASS RATIO WHEN THE ALTITUDE INCREASES. -The purpose of variable by-pass valves in a high bypass turbofan engine between the LP compressor and the HP compressor (HPC) is to: PREVENT FAN STALL AND LP COMPRESSO R STALL DURING ENGINE START AND LOW ROTOR SPEEDS. -The rating of electrical fuses is expressed in: AMPERES.-The purpose of the pack cooling fans in the air conditioning system is to: SUPP LY THE HEAT EXCHANGERS WITH COOLING AIR DURING SLOW FLIGHTS AND GROUND OPERATION. 3. supply diluted oxygen 4. decrease oxygen pressure from 1800 PSI (in the bottles) down to about 50-75 PSI (low pressure system) 2. supply oxygen on demand 5. -The purpose of the proximity of the emergency evacuation path marking system is to : GIVE ADDITIONAL GUIDANCE DURING AN EMERGENCY EVACUATION WITH A THICK SMOKE. 5 -The purpose of the venturi in a carburettor is to: CREATE THE SUCTION NECESSARY TO CAUSE FUEL TO FLOW THROUGH THE CARBURETTOR MAIN JETS. suppl y 100% oxygen 3. -The purposes of the oil and the nitrogen in an oleo-pneumatic strut are: THE OI L SUPPLIES THE DAMPING FUNCTION AND THE NITROGEN SUPPLIES THE SPRING FUNCTION -The Ram Air Turbine (RAT) provides emergency hydraulic power for: FLIGHT CONTRO LS IN THE EVENT OF LOSS OF ENGINE DRIVEN HYDRAULIC POWER. -The purpose of the regulator of a flight deck oxygen system is to: 1. trigger the continuous cabin altitude warning at 10000 ft cabin altitude The combination regrouping all the correct statements is: 2. -The reading on the oil pressure gauge is the: PRESSURE OF THE OIL ON THE OUTLET SIDE OF THE PRESSURE PUMP. 4. supply oxygen at emergency/p ositive pressure 6. . -The relationship between compression ratio of a piston engine and the required fuel octane rating is that the: HIGHER THE COMPRESSION RATIO.slight variation about the normal operating frequen cy.high oil temperature in the CSD. The combina tion that regroups all of the correct statements is: 1. THE HIGHER THE OCTANE RATING REQUIRED. -The reason for fitting thermal plugs to aeroplane wheels is that they: RELEASE AIR FROM THE TYRE IN THE EVENT OF OVERHEATING.low oil pressure in the CSD. 4 . THE HIGHER THE OCTANE RATING REQUIRED.excessive variation of voltage and kVAR. . -The reason for the fact that an aeroplane designed for long distances cannot si mply be used for short haul flights at higher frequencies is that: THE LIFETIME OF THE FATIGUE SE NSITIVE PARTS HAS BEEN BASED ON A DETERMINED LOAD SPECTRUM -The reason for the trim switch on a control column to consist of two separate s witches is: TO REDUCE THE PROBABILITY OF A TRIM-RUNAWAY -The reason for using inverters in an electrical system is: TO CHANGE DC INTO AC . -The reasons for disconnecting a constant speed drive (CSD) of an AC generator i n flight are: 1 . 3. -The replenishment of an onboard oxygen bottle must be done: WITH THE ENGINE(S) OFF. -The reason for having a low pressure fuel-cooled oil cooler in a recirculatory type oil system is to: COOL THE OIL AND HEAT THE FUEL. 2 . -The relationship between compression ratio of a piston engine and the required fuel octane rating is that the: HIGHER THE COMPRESSION RATIO. 3 .-The reason for a double switch on the elevator trim is: TO REDUCE THE PROBABILI TY OF A TRIM RUNAWAY. prevent ice formation. The value of the equivalent resistance (Req) so obtained is given by the following formula: 1/REQ = 1/R1 + 1/R2 -The richness of a fuel/air mixture ratio is the : REAL MIXTURE RATIO RELATIVE T O THE THEORETICAL RATIO. 2 . -The rotor blades of an axial compressor of a gas turbine engine are often mount ed on a disk or drum using a 'loose fit' because this: LIMITS DAMAGE TO THE BLADES DUE TO VIBRATION. -The sand filter located at the air intake of a gas turbine engine: REDUCES THE EFFICIENCY OF THE AIR INTAKE.will inflate each pneumatic boot for a few seconds. 4 . C2. 3.will repeat more than ten times per second . -The selection of bleed air to "ON" will cause: A DECREASE IN POWER AND AN INCRE ASE IN EXHAUST TEMPERATURE. The combination that regroups all of the correct statements is: 2. -The skip zone of HF-transmission will increase when the following change in cir cumstance occurs: HIGHER FREQUENCY AND HIGHER POSITION OF THE REFLECTING IONOSPHERIC LAYER -The 'slipstream effect' of a propeller is most prominent at: LOW AIRSPEEDS WITH HIGH POWER SETTING. 3 .can be triggered from the flight deck after icing has become visi ble. -The sequential pneumatic impulses used in certain leading edge de-icing devices : 1 . C3 . -The resistors R1 and R2 are connected in parallel.-The reservoirs of a hydraulic system can be pressurized: BY BLEED AIR FROM THE ENGINE. -The smoke detection in the aircraft cargo compartments is carried out by four s ensors: C1. refers to the: COLD AIR UNIT (AIR CYCLE MACHINE) ARRANGEMENT. Freefall. Auxiliary hydraulic system. 5. 4. 2. 5. -The term "Bootstrap". Compressed nitrogen. 3. at the selection of full power: 1 . -The static thrust of a turbo-jet. The combination containing all of the correct statements is: 2. -The take off of a jet aeroplane may be performed with "reduced thrust" in order to: REDUCE MAINTENANCE COSTS. -The speed of an asynchronous four-pole motor fed at a frequency of 400 Hertz is : 12000 REVOLUTIONS PER MINUTE. Th e repeating bell is activated when: THE C1 AND C2 SENSORS DETECT SMOKE.is independant of the outside air temperature The combination which regroups all the correct statements is : 1 3 th ex no of -The systems used for emergency extension of landing systems may comprise: 1. -The so-called "hot buses" or "direct buses" are: DIRECTLY CONNECTED TO THE BATT ERY.equals e product of the exhaust gas mass flow and the exhaust gas velocity 2 . Compressed oxygen.is equivalent to zero mechanical power since the aeroplane is t moving 4 . Co mpressed C0². -The term "pressure cabin" applies when an aeroplane: HAS THE MEANS TO MAINTAIN CABIN PRESSURE HIGHER THAN AMBIENT PRESSURE. -The term used to describe a permanent and cumulative deformation of the turbine blades in a gas turbine engine is: CREEP.is obtained by pressure of the haust gas on the ambient air 3 .and C4. 4. when used to identify a cabin air conditioning and pressu risation system. They are associated with the logic circuit as described in the annex. -The thermal efficiency of a diesel engine is higher than that of a petrol engin e because: THE . -The thermal efficiency of a gas turbine engine will increase with a: DECREASE I N AMBIENT AIR TEMPERATURE. -The two deformation modes that cause wing flutter are: TORSION AND BENDING. is mostly: A CONTINUOUS FLOW SYSTEM -The type of brake unit found on most transport aeroplanes is a: MULTIPLE DISK B RAKE. -The thrust reversers of jet engines may use clamshell doors in order to: CHANGE THE DIRECTION OF THE EXHAUST GAS STREAM. . -The turbine in a gas turbine engine generates shaft power using: EXPANSION OF H OT GAS FOLLOWED BY CONVERSION OF KINETIC ENERGY (VELOCITY) INTO (MECHANICAL) WORK. -The trim tab: REDUCES HINGE MOMENT AND CONTROL SURFACE EFFICIENCY. -The type of a aircraft oxygen system intended for use by passengers. -The thermal efficiency of a piston engine is about: 30% -The Throttle Lever Angle (TLA) information of a FADEC controlled gas turbine en gine is provided: TO THE ELECTRONIC ENGINE CONTROL UNIT BY A DIRECT ELECTRICAL WIRING CONNECTION. -The torque of an aeroplane engine can be measured at the: GEAR BOX WHICH IS LOC ATED BETWEEN THE ENGINE AND THE PROPELLER.COMPRESSION RATIO IS MUCH HIGHER. 4. -The useful work area in an ideal Otto engine indicator diagram is enclosed by t he following gas state change lines: 2 ADIABATIC AND 2 ISOCHORIC LINES. for ground starts.-The type of gate which requires all conditions with logic 1 for engagement is: AND. 6. 4. 5. throughout the oper ating range of the engine 2. 5.3.2. for in-flight relights The combination t hat regroups all of the correct statements is: 3 -The use of igniters is necessary or recommended on a turbo-jet:1. 6. under heavy precipitation or in icing conditions. -The use of too low an octane fuel may cause: DETONATION. during turbulence in flight. -The use of igniters in a gas turbine engine is required: 1. -The types of fuel tanks used on most modern transport aircraft are: INTEGRAL TA NKS. . -The type of hydraulic oil used in modern hydraulic systems is: SYNTHETIC OIL -The type of windings commonly used in DC starter motors are: SERIES WOUND. during engine acceleration 3. for in-flight relights. -The use of a hot air wing anti-icing system: DOES NOT AFFECT AERODYNAMIC PERFORMANCE OF THE WING AND CAUSES A REDUCTION IN MAXIMUM THRUST. -The type of hydraulic fluid which has the greatest resistance to cavitation is: SYNTHETIC FLUID. The combination whi ch regroups all of the correct statements is: 3. throughout th e operating range of the engine. for accelerations. 46 M . -The ventilation system in a fuel tank: PREVENTS LOW PRESSURE OR EXCESSIVE OVERPRESSURE IN THE TANK. -The wavelength of a non-directional beacon (NDB) at a frequency of 300 kHz is: 1000 METRES. -The wavelength of a radio signal transmitted at the frequency 118.. -The VHF Omnirange (VOR) uses the following wavelengths: METRIC. -The wavelength of a radio signal transmitted at the frequency of 75 MHz is: 4m -The wavelength of a radio transmitted on frequency 121. -The voltage regulator of a DC generator is connected in: SERIES WITH THE SHUNT FIELD COIL.5 3 M. -The viscosity of a hydraulic fluid should be: THE LOWEST TO MINIMIZE POWER CONS UMPTION AND RESISTANCE TO FLOW.95 MHz is: 2.-The vapour lock is: A STOPPAGE IN A FUEL FEEDING LINE CAUSED BY A FUEL VAPOUR BUBBLE. -The voltage of a fully charged lead-acid battery cell is: 2.2 VOLTS.7 MHz is: 2. -The very rapid magnetic field changes (flux changes) in the primary coil of a m agneto are accomplished by the: CONTACT BREAKER POINTS OPENING. -The VHF direction finder uses the following wavelengths: METRIC. powered by engines located under the wing. -To achieve control flutter damping the balance mass must be located: IN FRONT O F THE CONTROL SURFACE HINGE. -The wing ice protection system currently used for most large turboprop transpor t aeroplanes is a(n): PNEUMATIC SYSTEM WITH INFLATABLE BOOTS. -The wing of an aircraft in flight. COMPRESSION. EITHER PARTIALLY OR COMPLETELY. -The wing ice protection system currently used for most large jet transport aero planes is a(n): HOT AIR SYSTEM. i s subjected to a bending moment which causes its leading edge. AND THEN TENSION. -The working cycle of a four-stroke engine is: INDUCTION. POWER. from the wing root to the wing tip . -Thermal plugs are installed in: WHEEL RIMS. EX HAUST. -The wing of an aircraft in flight. -To achieve reverse thrust on a "big fan" turbine engine. AND THEN TENSION. .-The wing anti-ice system has to protect: THE LEADING EDGE OR THE SLATS. i s subjected to a bending moment due to thrust and drag. to operate in: COMPRESSION. it is necessary to: DE FLECT THE FAN THRUST. The loading on the front spar of the tors ion box from the wing root to the wing tip is: COMPRESSION. -The working principle of the anti-skid system is: REDUCTION OF THE BRAKE PRESSU RE AT THE SLOWER TURNING WHEELS. powered by engines located under the wing. -To achieve reverse thrust on a turbine engine with a high by-pass ratio, genera lly: THE FAN FLOW IS DEFLECTED. -To avoid the risk of tyre burst from overheating there is: A THERMAL PLUG THAT DEFLATES THE TYRE AT A SPECIFIC TEMPERATURE. -To ensure correct load sharing between AC generators operating in parallel: BOT H REAL AND REACTIVE LOADS MUST BE MATCHED. -To maintain a constant mixture at low and high power settings in a piston engin e, a carburettor is fitted with: A DIFFUSER (COMPENSATING JET). -To maintain the correct air/fuel ratio of a piston engine, independent of power setting, a carburettor is fitted with: A DIFFUSER (COMPENSATING JET). -To protect against excessive system pressure, a hydraulic system usually incorp orates: A HIGH PRESSURE RELIEF VALVE. -To reverse the direction of rotation of a shunt-type (parallel field) DC electr ic motor, it is necessary to: REVERSE THE POLARITY OF EITHER THE STATOR OR THE ROTOR. -Torsion in a wing can be caused by: POSITIVE SWEEP -Trimming of aileron and rudder in an irreversible flight control system: IS ACH IEVED BY ADJUSTING THE "ZERO FORCE POINT" OF THE FEEL SYSTEM. -Turbine blade stages may be classed as either "impulse" or "reaction". In an im pulse turbine stage: THE PRESSURE DROPS ACROSS THE STATOR BLADES AND REMAINS CONSTANT ACROSS THE ROTOR BLADES. -Turbine blade stages may be classed as either "impulse" or "reaction". In an im pulse blade section the pressure (i)... across the nozzle guide vanes and (ii)..... across the rotor blades: (I) DROPS (II) REMAINS CONSTANT -Turbine blade stages may be classed as either "impulse" or "reaction". In an im pulse blade section the pressure (i).. across the nozzle guide vanes and (ii).. across the rotor bla des: (I) DROPS (II) REMAINS CONSTANT -Tyre "creep" may be described as the: CIRCUMFERENTIAL MOVEMENT OF THE TYRE IN RELATION TO THE WHEEL FLANGE. -Under normal conditions (JAR 25) the cabin pressure altitude is not allowed to exceed: 8000 Ft -Under normal flight conditions, cabin pressure is controlled by: REGULATING THE DISCHARGE OF AIR THROUGH THE OUTFLOW VALVE(S). -Under normal running conditions a magneto draws primary current: FROM A SELF-CO NTAINED ELECTRO-MAGNETIC INDUCTION SYSTEM. -Using compressor bleed air to power systems: DECREASES AIRCRAFT PERFORMANCE -Vapour lock is: VAPORIZING OF FUEL PRIOR TO REACHING THE CARBURETOR -Vapour locking is caused by: VAPORIZING OF FUEL PRIOR TO THE ENGINE. -Variations in mixture ratios for carburettors are achieved by the adjustment of : FUEL FLOW. -Vents in oil tanks are primarily to: PREVENT EXCESSIVE PRESSURE FROM BUILDING U P IN TANK -Vibration sensors are used in a gas turbine engine to indicate: IMBALANCE OF ON E OR BOTH OF THE SPOOLS. -Viscosity is: THE TENDENCY OF A LIQUID OR GAS TO RESIST FLOW. -VLE is the maximum: FLIGHT SPEED WITH LANDING GEAR DOWN -VLO is the maximum: SPEED AT WHICH THE LANDING GEAR CAN BE OPERATED WITH FULL SAFETY. -What are the three elements of the fuselage structure of a large transport aero plane? SKIN, FRAMES, STRINGERS. -What is breathed in when using a passenger oxygen mask? CABIN AIR AND OXYGEN. -What is the load in the upper respectively lower girder of a spar of a cantilev er wing during straight and level flight? COMPRESSION IN THE UPPER GIRDER AND TENSION IN THE LOWER GIRDER. -What may happen during a continuous climb with a mixture setting fully rich? FO ULING OF SPARK PLUGS. -When a battery is almost fully discharged there is a tendency for the: VOLTAGE TO DECREASE UNDER LOAD. -When a bimetallic strip is used as a switch in a fire detection loop, a fire al arm is triggered after a its resistance increases. The combination regrouping all the correct statements: 1. -When a landing gear wheel is hydroplaning. the overexcitation protection device opens: THE EXCITER BREAKER. -When a conductor cuts the flux of a magnetic field: an electromotive force (EMF ) is INDUCED IN THE CONDUCTOR. -When a continuous loop wire type fire detection system is tested: THE WIRING AN D THE WARNING ARE TESTED. its resist ance decreases. the passenger breathes: A MIXTURE OF OXYGEN AND CABIN AIR. T HE GENERATOR BREAKER AND THE TIE BREAKER.delay. . the leakage current increases. -When a gas turbine engine is fitted with can-type combustion chambers: A TOTAL OF ONLY TWO IGNITERS ARE USUALLY FITTED SINCE THE CHAMBERS ARE INTER-CONNECTED. 2. THE GENERATOR BREAKER AND THE TIE BREAKER. -When a gas turbine engine accelerates from idle to take-off thrust and the comp ressor rpm is too high in comparison with the air inlet velocity. the leakage current d ecreases. 3. 3 -When a persistent top excitation limit fault on an AC generator connected to th e mains with another AC generator. its friction factor is equal to: 0 -When a part of a continuous loop fire detection system is heated: 1. the protection device opens: THE EXCITER CONTRO L RELAY. -When a persistent underexcitation fault is detected on an AC generator connecte d to the aircraft mains with another AC generator. The purpose of this delay is to: AVOID FALSE ALARMS IN CASE OF VIBRATIONS -When a cabin oxygen mask is pulled downwards. this may result in: A COMPRESSOR STALL. 4. -When a turbo-prop aeroplane decelerates during the intial part of the landing r oll. -When carrying out a battery condition check using the aircraft's voltmeter: A L OAD SHOULD BE APPLIED TO THE BATTERY IN ORDER TO GIVE A BETTER INDICATION OF CONDITION. a constant speed propeller within the beta range: PRODUCES NEGATIVE THRUST. -When a wing bends downwards. aileron flutter might occur if the aileron deflect s: UPWARDS. the : LOSS OF CON TINUITY WILL PREVENT ITS WORKING COMPONENTS FROM FUNCTIONING. the protection device opens the: GENERATOR BREAKER. BECAUSE THE LOCATION OF THE AILERON CENTRE OF GRAVITY LIES BEHIND THE HINGE LINE. -When an underspeed fault is detected on an AC generator connected to the aircra ft AC busbar. . -When altitude increases without adjustment of the mixture ratio. the piston eng ine performance is affected because of a : A DECREASE OF AIR DENSITY WITH A FUEL FLOW WHICH BECOMES TOO HIGH. -When a wing bends upwards. -When applying carburettor heating: THE MIXTURE BECOMES RICHER. -When an "open circuit" occurs in an electrical supply system. the percentage oxygen conte nt is: UNAFFECTED. aileron flutter might occur if the aileron deflects: DOWNWARDS. BECAUSE THE LOCATION OF THE AILERON CENTRE OF GRAVITY LIES BEHIND THE HINGE LINE. -When air is compressed for pressurization purposes. or when the engine is running at idle rpm on the grou nd. -When selected to normal. the pilot is: ABLE TO RADIOTELEPHONE. but still on th e rich side of the peak EGT. TO MAKE STARTING POSSIBLE AND TO COOL THE ENGINE SUFFICIENTLY WHEN IDLING. -When excessively leaning the mixture for a better fuel economy. the correct procedure is to: REDUCE MANIFOLD PRESSURE AND FULLY ENRICH THE MIXTURE. -When quick donning masks are in use. the following engine parameter(s) may exceed their normal operating ranges: CYLINDER HEAD AND EXHAUST GAS TEMPERATURE. the propeller is said to be: FEATHERED. the level in the reservoir will: DECREASE SLIGHTLY. excessive lean ing will cause: HIGH CYLINDER HEAD TEMPERATURE -When powering up a hydraulic system. the mixture is: RICH. -When starting the engine. -When detonation is recognised in a piston engine. a piston engine is stopped and the propeller blade angle is nea r 90°.-When changing power on engines equipped with constant-speed propeller. the oxygen/air ratio of the mixture supplied by the co ckpit oxygen system regulator: INCREASES WHEN THE ALTITUDE INCREASES. . -When in flight. the angle of attack o f a fixed pitch propeller: REDUCES. -When increasing true airspeed with a constant engine RPM. engine o verload is avoided by: INCREASING THE RPM BEFORE INCREASING THE MANIFOLD PRESSURE. -When leaning the mixture for the most economic cruise fuel flow. the blade angle of a constant speed propeller will (RPM and throttle levers are not moved): INCREASE. the structural elements of the w ing. -When the AC voltage across a capacitor is kept constant and the frequency is in creased. which carry the bending moment. -When the pilot moves the mixture lever of a piston engine towards a lean positi on the: AMOUNT OF FUEL ENTERING THE COMBUSTION CHAMBER IS REDUCED. . equipped with evacuation slides in the armed position.. are: THE SPARS. THE COCKPIT CREW IS SUPPLIED WITH A MIXTURE OF OXYGEN AND CABIN AIR . -When the oxygen system of a large aeroplane is used: WITH THE SETTING ON "NORMA L". the reactive loads are balanc ed by means of the: ENERGIZING CURRENT. VARIES THE FIELD EXCITATION CURRENT OF THE GENERATORS. -When the AC generators are connected in parallel. the current through the capacitor will: INCREASE. -When the door of a transport aeroplane. -When the combustion gases pass through a turbine the: PRESSURE DROPS. -When two DC generators are operating in parallel. -When the AC generators are connected in parallel. is opened from the outside the slide: IS DISARMED AUTOMATICALLY. IN CONJUNCTION WITH THE VOLTAGE REGULATORS.-When TAS increases. control of load sharing is ac hieved by: AN EQUALISING CIRCUIT WHICH. -When the wing skin is not able to carry loads. the reactive loads are balanc ed by means of the: EXCITATION CURRENT. The speed remains constant in flow direction. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. The stat ic temperature decreases in flow direction: I IS INCORRECT.-Which of the following parameters remains constant in a divergent (subsonic) ga s turbine engine intake? TOTAL TEMPERATURE. The stat ic temperature increases in flow direction: I IS INCORRECT. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. II IS CORRECT. The dynamic pressure decreases in flow direction. The total temperature remains constant in flow direction: I IS CORRECT. II IS INCORRECT. II. II IS CORRECT. II. II. II. II IS CORRECT. The dynamic pressure increases in flow direction. The total temperature increases in flow direction: I IS CORRECT. The static pressure remains constant in flow direction. Th e total temperature . II IS CORRECT. The dynamic pressure increases in flow direction. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. The total pr essure remains constant in flow direction: I IS INCORRECT. II IS INCORRECT. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. The static pressure increases in flow direction. The total pressure remains constant in flow direction: I IS CORRECT. The static pressure increases in flow direction. II. II. II. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. The speed decreases in flow direction. II. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. II IS CORRECT. The stat ic temperature increases in flow direction: I IS CORRECT. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. II. The speed remains constant in flow direction. There is no need for a gust lock on irreversible flight controls. II. CONTROL COMPRESSOR AIRFLOW. II IS INCORRECT. -Which of the following statements regarding variable inlet guide vanes (VIGVs) and variable stator vanes (VSVs) on a high-bypass engines is correct? VIGVS ARE LOCATED AT THE FRONT OF THE HP COMPRESSOR AND. II IS INCORRECT. The total pr essure decreases in flow direction: I IS INCORRECT. The total pressure decreases in flow direction: I IS CORRECT. II. TOGETHER WITH THE VSVS. T he static temperature remains constant in flow direction: I IS INCORRECT. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. II. -Which of these statements about a gust lock system are correct or incorrect? I. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. The speed decreases in flow direction. The stat ic temperature decreases in flow direction: I IS CORRECT. II. II IS INCORRECT. The dynamic pressure remains constant in flow direction. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I.decreases in flow direction: I IS INCORRECT. II. II IS INCORRECT. Re versible flight controls . II IS INCORRECT. -Which of these statements about a gust lock system are correct or incorrect? I. The total temperature increases in flow direction: I IS INCORRECT. II. There should be suitable design precautions to prevent flight with the gust lock engaged. The static pressure decreases in flow direction. The dynamic pressure decreases in flow direction. -Which of the following statements is correct about the flow in a divergent (sub sonic) gas turbine engine intake? I. There is no need for a gust loc k on manual flight controls: I IS CORRECT. II IS INCORRECT. II IS INCORRECT. II. Th ere is no need for a gust lock on reversible flight controls: I IS CORRECT. There is no need for a g ust lock on reversible flight controls: I IS INCORRECT. II. The pressure rises across the nozzle guide vanes. The pressure remains constant across the nozzle guide vanes. -Which of these statements about a gust lock system are correct or incorrect? I. The pressure rises across the rotor blades: I IS INCORRECT. II IS CORRECT. II IS INCORRECT. II IS CORRECT.should have a gust lock: I IS CORRECT. There should be suitable design precautions to prevent flight with the gust lock engaged. -Which of these statements about an aeroplane's hydraulic system is correct? THE FILTERS. -Which of these statements about an impulse turbine are correct or incorrect? I. II. There is no need for a gust lock on irreversible flight controls. . A gust lock can be used in flight to reduce the effects of turbulence. II IS INCORRECT. II IS INCORRECT. II. -Which of these statements about an impulse turbine are correct or incorrect? I. AND THE FIRE SHUT-OFF VALVE ARE SAFETY FEATURES INSTALLED IN THE SYSTEM. The pressure rises across th e rotor blades: I IS INCORRECT. II IS CORRECT. The pressure remains constant across the nozzle guide vanes. -Which of these statements about a gust lock system are correct or incorrect? I. -Which of these statements about an impulse turbine are correct or incorrect? I. THE BY-PASS VALVE(S). Manual flight controls should h ave a gust lock: I IS CORRECT. Irreversible flight controls should have a gust lock. -Which of these statements about a gust lock system are correct or incorrect? I. THE PRESSURE RELIEF VALVE(S). The pressure remains constan t across the rotor blades: I IS INCORRECT. II. II IS INCORRECT. II. -Which of these statements about a gust lock system are correct or incorrect? I. II IS INCORRECT. There is no need for a gust lock on manual flight controls: I IS INCORRECT. II. -Which of these statements about an impulse turbine are correct or incorrect? I. II IS CORRECT. -Which of these statements about an reaction turbine are correct or incorrect? I . II IS CORRECT. II IS INCORRECT. II IS INCORRECT. The pressure remains constant across the roto r blades: I IS INCORRECT. The pressure remains constan t across the rotor blades: I IS INCORRECT. II IS INCORRECT. The pressure remains constant across the nozzle guide vanes. II. II IS INCORRECT. The pressure remains constant across the nozzle guide vanes. The pressure drops across th e rotor blades: I IS INCORRECT. -Which of these statements about an impulse turbine are correct or incorrect? I. -Which of these statements about an impulse turbine are correct or incorrect? I. The pressure rises across the nozzle guide vanes. The pressure rises across th e rotor blades: I IS INCORRECT. -Which of these statements about an impulse turbine are correct or incorrect? I. The pressure drops across the nozzle guide vanes. -Which of these statements about an reaction turbine are correct or incorrect? I . The pressure drops across the nozzle guide vanes. . The pressure remains constant across the roto r blades: I IS CORRECT. The pressure rises across the rotor blades: I IS CORRECT. The pressure drops across the nozzle guide vanes. The pressure drops across the rotor blades: I IS INCORRECT. II. II. II. The pressure rises across the nozzle guide vanes. II. II. II. The pressure drops across the rotor blades: I IS CORRECT. II. -Which of these statements about an impulse turbine are correct or incorrect? I. The pressure remains constant across the nozzle guide vanes. II IS INCORRECT. -Which of these statements about an impulse turbine are correct or incorrect? I. II IS INCORRECT. II. II. The pressure rises across the rotor blades: I IS INCORRECT. II. The pressure remains constant across the roto r blades: I IS CORRECT. II IS INCORRECT. II IS INCO RRECT. -Which of these statements about chemical oxygen generators are correct or incor rect? I. Chemical . II IS CORRECT. II. II. II IS INCORRECT. The pressure drops across the nozzle guide vanes. II IS INCORRECT. The pressure drops across the nozzle guide vanes.-Which of these statements about an reaction turbine are correct or incorrect? I . -Which of these statements about an reaction turbine are correct or incorrect? I . II. -Which of these statements about an reaction turbine are correct or incorrect? I . The pressure drops across th e rotor blades: I IS INCORRECT. The pressure drops across the rotor blades: I IS INCORRECT. once activated. The pressure rises across the nozzle guide vanes. The pressure drops across the rotor blades: I IS CORRECT. The pressure rises across the nozzle guide vanes. -Which of these statements about chemical oxygen generators are correct or incor rect? I. The oxygen supp ly of chemical oxygen generators. II IS INCORRECT. The pressure rises across the nozzle guide vanes. The pressure rises across the rotor blades: I IS CORRECT. -Which of these statements about an reaction turbine are correct or incorrect? I . -Which of these statements about an reaction turbine are correct or incorrect? I . -Which of these statements about an reaction turbine are correct or incorrect? I . The pressure drops across the nozzle guide vanes. Chemical oxygen generators are often used to supply passenger oxygen. The pressure remains constant across the nozzle guide vanes. II. II IS CORRECT. II. -Which of these statements about an reaction turbine are correct or incorrect? I . The pressure remains constant across the roto r blades: I IS INCORRECT. can be switched off: I IS CORRECT. II IS CORRECT. A compressor stall is most likely to occur when the air flow stagnates in the fron t stages of the . -Which of these statements about composite and metal structures are correct or i ncorrect? I. II. once activated. II. -Which of these statements about chemical oxygen generators are correct or incor rect? I. -Which of these statements about chemical oxygen generators are correct or incor rect? I. t he strength is the same in all directions. II. II IS C ORRECT. II IS CORRECT. cannot be switched off: I IS CORRECT. The oxygen s upply of chemical oxygen generators. II. II IS INCORRECT . once activated. II IS CORRECT. II IS INCORRECT. cannot be switched off: I IS INCORRECT. A compressor stall is most likely to occur in a compressor designed for a high pressure ratio operatin g at high RPM. For a structural component with given dimensions composite materials enable a structur al component's strength to be tailored to the direction of the load. -Which of these statements about compressor stall are correct or incorrect? I. In a structural component with given dimensions constructed of composite materials. II. Composite materials enable structures with lower str ength/weight ratio than metal structures: I IS INCORRECT. The oxygen supp ly of chemical oxygen generators. The oxygen s upply of chemical oxygen generators. -Which of these statements about composite and metal structures are correct or i ncorrect? I. II. t he strength is the same in all directions. In a structural component with given dimensions constructed of composite materials. II IS CORRECT. Chemical oxygen generators are often used to supply passenger oxygen. Composite materials en able structures with higher strength/weight ratio than metal structures: I IS CORRECT. Composite materials enable structures with higher st rength/weight ratio than metal structures: I IS INCORRECT. Chemical oxygen generators are used to supply the cockpit oxygen system. once activated. II. For a structural component with given dimensions composite materials enable a structur al component's strength to be tailored to the direction of the load. II IS IN CORRECT. Composite materials en able structures with lower strength/weight ratio than metal structures: I IS CORRECT. can be switched off: I IS INCORRECT.oxygen generators are used to supply the cockpit oxygen system. -Which of these statements about composite and metal structures are correct or i ncorrect? I. -Which of these statements about composite and metal structures are correct or i ncorrect? I. II. compressor: I IS INCORRECT. . II IS INCORRECT. A rudder ratio changer system limits both rudder and rudder pedal deflection as the IAS increases. II. A compressor stall is most likely to occur when the air flow stagnates in the fron t stages of the compressor: I IS CORRECT. A sandwich structural part is not suitable for absorbing concentrated loads: I IS CORRECT. A compressor stall is most likely to occur in a compressor designed for a high pressure ratio operatin g at high RPM.-Which of these statements about compressor stall are correct or incorrect? I. A variable stop system reduces the rudder deflection for a given rudder pedal deflection as the IAS inc reases: I IS INCORRECT. II. II IS CORRECT. A variable stop system limits both rudder and rudder pedal deflection as the IAS i ncreases: I IS CORRECT. A compressor stall is most likely to occur in a compressor designed for a high pressure ratio operatin g at low RPM. A rudder ratio changer system reduces the rudder deflection for a given rudder pedal deflection as the IAS increases. II IS CORRECT. A compressor stall is most likely to occur when the air flow stagnates in the rear stages of the compressor: I IS CORRECT. -Which of these statements about sandwich structural parts are correct or incorr ect? I. II. II IS CORRECT. II. -Which of these statements about compressor stall are correct or incorrect? I. A rudder ratio changer system reduces the rudder deflection for a given rudder pedal deflection as the IAS increases. II IS INCORRECT. A variable stop system limits both rudder and rudder pedal deflection as the IAS d ecreases: I IS CORRECT. A sandwich structural part consists of two thin sheets enclosing a light core material. II. A compressor stall is most likely to occur in a compressor designed for a high pressure ratio operatin g at low RPM. -Which of these statements about rudder limiting are correct or incorrect? I. II. -Which of these statements about rudder limiting are correct or incorrect? I. . -Which of these statements about compressor stall are correct or incorrect? I. II IS INCORRECT. II IS CORRECT. II. A compressor stall is most likely to occur when the air flow stagnates in the rear stages of the compressor: I IS INCORRECT. -Which of these statements about rudder limiting are correct or incorrect? I. II IS INCORRECT. -Which of these statements about sandwich structural parts are correct or incorr ect? I. II. safe life implies the structure will never fail during a declared time period or number of cycles: I I S INCORRECT. A sandwich structural part is suitable for absorbing concentrated loads: I IS CORRECT. s afe life implies the structure will never fail during a declared time period or number of cycles: I IS CORRECT. -Which of these statements about structural design principles are correct or inc orrect? I. A sandwich structural part i s not suitable for absorbing concentrated loads: I IS INCORRECT. In structural design. -Which of these statements about structural design principles are correct or inc orrect? I. A safe life structure is bas ed on a declared number of cycles or time period: I IS CORRECT. II IS CORRECT. II. -Which of these statements about sandwich structural parts are correct or incorr ect? I. II IS INCORRECT. fail safe implies parallel structural parts. -Which of these statements about structural design principles are correct or inc orrect? I. II. In structural design. II. The safe l ife principle is based on the replacement of parts after a given number of cycles or flight hours: I IS CO RRECT. In structural design. In structural desig n. A sandwich structural part i s suitable for absorbing concentrated loads: I IS INCORRECT. A sandwich structural part consists of fibres and a resin. The damage tolerance principle takes cracking of the structure into account. A sandwich structural part consists of fibres and a resin. II IS INCORRECT. II. -Which of these statements about structural design principles are correct or inc orrect? I. -Which of these statements about sandwich structural parts are correct or incorr ect? I. A safe life structu re is based on a declared time period or number of cycles: I IS INCORRECT. II. In structural design. II. II IS CORRECT. II IS INCORRECT. -Which of these statements about structural design principles are correct or inc orrect? I. fail safe implies the structure will never fail. A sandwich structural part consists of two thin sheets enclosing a light core material. II IS INCORRECT. In structural design. II IS CORRECT. . II. II IS CORRECT. fail safe implies the structure will never fail. fail safe implies redundant load paths. II. The zero force position of the control co lumn does not change when using the elevator trim. II IS CORRECT. II IS INCORRECT. The zero force position of the control co lumn does not change when using the elevator trim. The zero force position of the control co lumn changes when using the elevator trim. . -Which of these statements about trimming in a irreversible flight control syste m of a conventional aeroplane are correct or incorrect? I. The zero force position of the control wheel d oes not change when using the aileron trim: I IS CORRECT. The damage tolerance principle assumes cracks in the structure will never occur. II. II IS CORRECT. A sandwich structura l part is unsuitable for absorbing concentrated loads: I IS INCORRECT.-Which of these statements about structural design principles are correct or inc orrect? I. -Which of these statements about trimming in a irreversible flight control syste m of a conventional aeroplane are correct or incorrect? I. The zero force position of the control wheel c hanges when using the aileron trim: I IS CORRECT. -Which of these statements about trimming in a irreversible flight control syste m of a conventional aeroplane are correct or incorrect? I. The zero force position of the control wheel does n ot change when using the aileron trim: I IS INCORRECT. II. II. The sa fe life principle is based on the replacement of parts after a given number of cycles or time period: I IS INCORRECT. RIBS AND WING SKIN REINFORCED BY STRINGERS. II IS INCORRECT. The main function of the core material is sound insulation. II IS INCORRECT. -Which of these statements about trimming in a irreversible flight control syste m of a conventional aeroplane are correct or incorrect? I. The zero force position of the control co lumn changes when using the elevator trim. II IS CORRECT. II. II. -Which of these statements about the wing structure is correct? A TORSION BOX IS FORMED BY WING SPARS. I IS INCORRECT. II. A sandwich structura l part is well suited for absorbing concentrated loads. II IS CORRECT. -Which of these statements concerning a sandwich structural part are correct or incorrect? I. The zero force position of the control wheel change s when using the aileron trim: I IS INCORRECT. -Which of these statements concerning a sandwich structural part are correct or incorrect? I. The main function of the core material is sound insulation. -Which of these statements concerning a sandwich structural part are correct or incorrect? I. -Which of these statements regarding most gust lock systems is correct? WHEN THE GUST LOCK IS ON THERE IS PROTECTION TO PREVENT TAKE-OFF. II IS CORRECT. . -Which one of the following factors would be most likely to increase the possibi lity of detonation occurring within a piston engine? HIGH CYLINDER HEAD TEMPERATURE. Cockpit side windows are usually defogged only: I IS INCORRECT. II. II IS INCORRECT. Cockpit windows never have an additional speed restriction. On some aeroplanes the cockpit windows have an additional speed restriction. -Which of these statements regarding cockpit windows are correct or incorrect? I . II. related to bird impact. II IS CORRECT. The main function of the core material is to stabilise the covering sheets. II IS INCORRECT. Cockpit side windows are usually defogged onl y: I IS CORRECT. A sa ndwich structural part is well suited for absorbing concentrated loads: I IS CORRECT. II IS INCORRECT. when window heating is inoperative. -Which of these statements concerning a sandwich structural part are correct or incorrect? I. II IS CORRECT. related to bird impact. -Which of these statements regarding cockpit windows are correct or incorrect? I . when window heating is inoperative. II. when window heating is inoperative. when window heating is inoperative. A sa ndwich structural part is unsuitable for absorbing concentrated loads: I IS CORRECT. II. II. Cockpit windows never have an additional speed restriction. related to bird impact. On some aeroplanes the cockpit windows have an additional speed restriction. -Which of these statements regarding cockpit windows are correct or incorrect? I . Cockpit side windows are always provided with a de-icing system: I IS CORRECT. Cockpit side windows are always provided with a de-icing system : I IS INCORRECT. II. -Which of these statements regarding cockpit windows are correct or incorrect? I . The main function of the core material is to stabilise the covering sheets. related to bird impact. The HP spool speed increases. II. II IS INCORRECT. II IS INCORRECT -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. when the power setting is increased? I. T he speed increases in flow direction. II. The gas generator speed increas es. -Which statement is correct about the flow in a divergent jet engine inlet? I.-Which one of the following factors would be most likely to increase the possibi lity of detonation occurring within a piston engine? USING TOO LEAN A FUEL/AIR MIXTURE -Which one of the following factors would be most likely to increase the possibi lity of detonation occurring within a piston engine? HIGH CYLINDER HEAD TEMPERATURE. The EGT remains constant: I IS CORRECT. The EGT decreases: I IS CORRECT . when the power setting is increased? I. -Which statement is correct concerning the effect of the application of carburet tor heat? THE DENSITY OF THE AIR ENTERING THE CARBURETTOR IS REDUCED. when the power setting is increased? I. THUS ENRICHING THE FUEL/AIR MIXTURE. -Which statement is correct concerning the effect of the application of carburet tor heat? THE DENSITY OF THE AIR ENTERING THE CARBURETTOR IS REDUCED. The total pressure increases in flow direction: I IS INCORRE CT. The EGT . THUS ENRICHING THE FUEL/AIR MIXTURE. II. II IS INCORRECT. The gas generator speed decreas es. T he static pressure remains constant in flow direction. The total temperature remains constant i n flow direction: I IS INCORRECT. I I. -Which statement is correct about the flow in a divergent jet engine inlet? I.II. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. II IS CORRECT. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. when the power setting is increased? I. . when the power setting is increased? I. The EGT decreases: I IS CORRECT. The gas generator speed remains constant. II IS CORRECT. The gas generator speed remains constant. II. II IS CORRECT.remains constant: I IS INCORRECT. when the power setting is increased? I. when the power setting is increased? I. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. I I. The gas generator speed increas es. II. II IS CORRECT. The EGT increases: I IS INCORRECT. The gas generator speed increas es. when the power setting is increased? I. II IS CORRECT. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. The gas generator speed decreas es. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. II IS INCORRECT. The EGT increases: I IS INCORRECT. II IS CORRECT. II. The EGT increases: I IS CORRECT. II IS CORRECT. The HP spool speed decreases. II. when the power setting is increased? I. The EGT decreases: I IS INCORRECT. II. I I. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. The EGT remains constant: I IS CORRECT. The HP spool speed remains cons tant. when the power setting is increased? I. when the power setting is decreased? I. II. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. The HP spool speed increases. II IS INCORRECT. The EGT increases: I IS CORRECT. II IS INCORRECT. The EGT increases: I IS INCORRECT. when the power setting is increased? I. The gas generator speed decreas es. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. II IS INCORRECT. II. II. The gas generator speed remains constant. when the power setting is increased? I. when the power setting is increased? I. II IS INCORRECT. The flash point for Jet A is at a higher temperature than that for Jet B: I IS CORRECT. II. The EGT remains constant: I IS INCORRECT. The freezing point for Jet A is at a lower tempe rature than that for Jet B. The gas generator speed decreas es. The freezing point for Jet A is at a lower tempe for Jet B. CORRECT. The gas generator speed increas es. The EGT decreases: I IS INCORRECT. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. The flash point for Jet A is at a lower temperature than that for Jet B: I IS INCORRECT. II. II. when the power setting is increased? I. The EGT increases: I IS INCORRECT. The flash I IS INCORRECT. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. -Which statement rature than that point for Jet A is at a higher temperature than that for Jet B: II IS is correct? I. The EGT decreases: I IS INCORRECT. . II IS INCORRECT. II. II IS CORRECT. II IS INCORRECT. II IS INCORRECT. -Which statement is correct? I. I I.-Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. when the power setting is increased? I. The HP spool speed decreases. -Which statement is correct for a gas turbine engine with a constant speed prope ller and free power turbine. -Which statement is correct? I. The EGT decreases: I IS CORRECT. II IS CORRECT. The freezing point for Jet A is at a higher temp erature than that for Jet B. II. COMPRESSION IN THE LOWER SURFACE. The freezing point for Jet A is at a lower tempe rature than that for Jet B. The freezing point for Jet A is at about the sam e temperature as that for Jet B. . The flash point for Jet A is at about the same temperature as that for Je t B: I IS INCORRECT. II IS INCORRECT. THUS CAUSING THE SAFETY RELIEF VALVES TO OPEN. II. II.-Which statement is correct? I. II IS CORRECT. one magneto fails completely. -With regard to a twin spool turbofan. -Which statement is correct? I. when detonation is recognised. -Windshield heating of a transport aeroplane is: ESSENTIAL TO IMPROVE THE STRENG TH OF THE COCKPIT WINDOWS. -Whilst in level cruising flight. II. during flight at normal c ruising speed. you: REDUCE MANIFOLD PRESS URE AND ENRICH THE MIXTURE -With an aircraft fitted with a fixed pitch propeller. -Which statement is correct? I. -Whilst stationary on the ground in a hangar the most important loads on a canti lever wing are: TENSION IN THE UPPER SURFACE. The freezing point for Jet A is at a higher temp erature than that for Jet B. This will first cause: LOSS OF APPROXIMATELY 100 RPM. The flash point for Jet A is at a lower temperature than that for Jet B: I IS CORRECT. -With a piston engine. an aeroplane with a pressurised cabin experien ces a malfunction of the pressure controller. an abortive start (hung start) will resul t in: N2 SPEED STABILISING AT A LOWER THAN NORMAL RPM AND A SUBSEQUENT INCREASE IN EGT. II IS INCORRECT. If the cabin rate of climb indicator reads -200ft/min: THE DIFFERENTIAL PRESSURE WILL RISE TO ITS MAXIMUM VALUE. The flash point for Jet A is at a higher temperature than that fo r Jet B: I IS INCORRECT. . -With respect to a piston engine aircraft. -With regard to pneumatic mechanical devices that afford ice protection the only correct statement is: THEY CAN ONLY BE USED AS DE-ICING DEVICES.-With regard to an aircraft structure. 'fail safe' is one: IN WHICH THE LOAD IS CARRIED BY OTHER COMPONENTS IF A PART OF THE STRUCTURE FAILS. ice in the carburettor: MAY FORM AT O AT'S HIGHER THAN +10°C. -With which instrument(s) do you monitor the power output of an aeroplane fitted with a fixed pitch propeller? RPM INDICATOR.
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