DGCA Module 15 Part 1 PDF

WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material...

WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material 15.1 Fundamentals 15.2 Engine Performance 15.3 Inlet Module 15, GAS TURBINE ENGINE. C. Tt7. Ans.- Pt7. Explanation. Jeppesen A&P Powerplant Textbook 1(www.dgcaquestionpapers.in), Like us on Facebook @ fb/DGCAQuestionPapers ( All CAR 66 Module Exam QP Available 3-5. 15.1 GAS TURBINE ENGINE Fundamentals. Q. 6. In a free turbine. A. there is a clutch between compressor and power Q. 1. On an axial flow, dual compressor forward fan output shaft. engine, the fan turns the same speed as the. B. there is a direct drive with a free-wheel unit. C. there is no mechanical connection with the A. low pressure turbine. compressor. B. high pressure compressor. Ans.- there is no mechanical connection with the C. forward turbine wheel. compressor. Ans.- low pressure turbine. Explanation. Rolls Royce The Jet engine Page 5 Explanation. Rolls Royce The Jet engine Page 6 refers. refers. Q. 7. Bernoulli's Theorem states that at any point in Q. 2. A turbo jet engine gives. a flow of gas. A. large acceleration to a small mass of air. A. the static pressure and dynamic pressure are equal. B. large acceleration to a large weight of air. C. small acceleration to a large mass of air. B. the static pressure is less than the dynamic pressure. Ans.- large acceleration to a small mass of air. Explanation. Rolls Royce The Jet engine Page 2/3 C. the total energy remains constant. refer. Ans.- the total energy remains constant. Explanation. See Chapter 2 of Rolls Royce The Jet Engine. Q. 3. The basic gas turbine engine is divided into two main sections: the cold section and the hot section. Q. 8. The working fluid of a gas turbine engine is. A. The cold section includes the engine inlet, compressor, and turbine sections. A. gasoline. B. The hot section includes the combustor, diffuser, and B. kerosene. exhaust. C. air. C. The hot section includes the combustor, turbine, and Ans.- air. exhaust. Explanation. Kerosene provides the energy to drive Ans.- The hot section includes the combustor, turbine, the air. and exhaust. Explanation. NIL. Q. 9. Which statements are true regarding aircraft engine propulsion?. Q. 4. A jet engine derives its thrust by. A. Turbojet and turbofan engines impart a relatively A. drawing air into the compressor. large amount of acceleration to a smaller mass of air. B. impingement of the propelling gases on the outside B. In modern turboprop engines, nearly 50 percent of air. the exhaust gas energy is extracted by turbines to drive C. reaction of the propelling gases. the propeller and compressor with the rest providing Ans.- reaction of the propelling gases. exhaust thrust. Explanation. Newtons third law applies- Rolls Royce C. An engine driven propeller imparts a relatively small The Jet engine Page 2/3 refers. amount of acceleration to a large mass of air. Ans.- An engine driven propeller imparts a relatively small amount of acceleration to a large mass of air. Q. 5. Which of the following might be used to Explanation. Jeppesen A&P Powerplant Textbook identify turbine discharge pressure?. 3-43. Page A. Pt7. B. Pt2. DOWNLOAD OUR MOBILE APP FROM PLAY STORE @DGCA QUESTION PAPERS IF YOU HAVE PREVIOUS SESSION QUESTION PAPERS, SHARE WITH US AT [email protected]  WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material 15.1 Fundamentals 15.2 Engine Performance 15.3 Inlet Q. 10. As subsonic air flows through a convergent nozzle the velocity. A. decreases. Q. 16. The term Pt7 means. 2(www.dgcaquestionpapers.in), Like us on Facebook @ fb/DGCAQuestionPapers ( All CAR 66 Module Exam QP Available B. increases. A. pressure and temperature at station No. 7. C. remains constant. B. the total pressure at station No. 7. Ans.- increases. C. the total inlet pressure. Explanation. Bernoulli's Theorem again. Ans.- the total pressure at station No. 7. Explanation. NIL. Q. 11. In a twin spool compressor system, the first stage turbine drives the. Q. 17. What section provides proper mixing of the A. N2 compressor. fuel and efficient burning of the gases?. B. N1 and N2 compressors. A. Diffuser section and combustion section. C. N1 compressor. B. Combustion section and compressor section. Ans.- N2 compressor. C. Combustion section only. Explanation. Jeppesen A&P Powerplant Textbook Ans.- Combustion section only. 3-18. Explanation. Jeppesen A&P Powerplant Textbook 3-21. Q. 12. At what point in an axial flow turbojet engine will the highest gas pressures occur?. Q. 18. Of the following, which engine type would A. At the compressor outlet. most likely have a noise suppression unit installed?. B. At the turbine entrance. C. Within the burner section. A. Turboprop. Ans.- At the compressor outlet. B. Turbojet. Explanation. Jeppesen A&P Powerplant Textbook C. Turboshaft. 3-20. Ans.- Turbojet. Explanation. Jepperson Gas Turbine Powerplants Page 3-57 refers. Q. 13. Which of the following units are generally used to measure aircraft noise?. A. Effective perceived noise decibels (E P N d B). Q. 19. The pressure of supersonic air as it flows B. Decibels (dB). through a divergent nozzle. C. Sound pressure. A. decreases. Ans.- Effective perceived noise decibels (E P N dB). B. increases. Explanation. Rolls Royce The jet engine page 199 C. is inversely proportional to the temperature. refers. Ans.- decreases. Explanation. A&P Airframe Textbook Page 2-31 and 2-32. Q. 14. The diffuser section is located between. A. the burner section and the turbine section. Q. 20. The symbol for designating the speed of a LP B. station No. 7 and station No. 8. compressor in a twin spool engine is. C. the compressor section and the burner section. A. N. Ans.- the compressor section and the burner section. B. NG. Explanation. Jeppesen A&P Powerplant Textbook C. N1. 3-20. Ans.- N1. Explanation. Jepperson Gas Turbine Powerplants Page 12-13 refers to N1 for LP N2 for H P. Q. 15. If the LP shaft shears. A. turbine runaway occurs. B. compressor overspeed occurs. Q. 21. A turbojet engine is smoother running than a C. compressor underspeed occurs. piston engine because. Ans.- turbine runaway occurs. A. the lubrication is better. Page Explanation. The turbine drives the LP compressor B. it runs at a lower temperature. or fan. C. it has no reciprocating parts. DOWNLOAD OUR MOBILE APP FROM PLAY STORE @DGCA QUESTION PAPERS IF YOU HAVE PREVIOUS SESSION QUESTION PAPERS, SHARE WITH US AT [email protected]  WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material 15.1 Fundamentals 15.2 Engine Performance 15.3 Inlet Ans.- it has no reciprocating parts. C. Every body persists in its state of rest, or of motion in Explanation. NIL. a straight line, unless acted upon by some outside force. 3(www.dgcaquestionpapers.in), Like us on Facebook @ fb/DGCAQuestionPapers ( All CAR 66 Module Exam QP Available Ans.- Every body persists in its state of rest, or of Q. 22. A gas turbine engine comprises which three motion in a straight line, unless acted upon by some main sections?. outside force. A. Compressor, diffuser, and stator. Explanation. NIL. B. Turbine, compressor, and combustion. C. Turbine, combustion, and stator. Ans.- Turbine, compressor, and combustion. Q. 28. A high bypass engine results in. Explanation. NIL. A. overall slower airflow and greater propulsive efficiency. B. overall faster airflow. Q. 23. When a volume of air is compressed. C. greater propulsive efficiency. Ans.- overall slower airflow and greater propulsive A. heat is gained. efficiency. B. no heat is lost or gained. Explanation. Jepperson Gas Turbine Powerplants C. heat is lost. Page 2-29 refers. Ans.- no heat is lost or gained. Explanation. Jepperson Gas Turbine Powerplants Page 2-18 refers - assuming adiabatic. Q. 29. Bernoulli's Theorem states that at any point in a flow of gas. A. the static pressure and dynamic pressure are equal. Q. 24. The pressure of subsonic air as it flows through a convergent nozzle. B. the static pressure is less than the dynamic pressure. A. increases. B. remains constant. C. the total energy remains constant. C. decreases. Ans.- the total energy remains constant. Ans.- decreases. Explanation. NIL. Explanation. NIL. Q. 30. The Brayton cycle is known as the constant. Q. 25. If a volume of a mass of air is 546 cubic feet at 273K, at 274K it will be. A. temperature cycle. A. 2 cubic feet greater. B. mass cycle. B. 1/273 less by weight. C. pressure cycle. C. 2 cubic feet smaller. Ans.- pressure cycle. Ans.- 2 cubic feet greater. Explanation. NIL. Explanation. NIL. Q. 31. In a choked nozzle, velocity increases, and. Q. 26. In what section of a turbojet engine is the jet nozzle located?. A. density decreases. A. Exhaust. B. pressure decreases. B. Turbine. C. pressure increases. C. Combustion. Ans.- pressure increases. Ans.- Exhaust. Explanation. Jepperson Gas Turbine Powerplant Explanation. NIL. Page 2-23. As the nozzle goes sonic the pressure starts to increase as a result of the shock wave. Q. 27. Newton's First Law of Motion, generally termed the Law of Inertia, states:. Q. 32. Using standard atmospheric conditions, the A. To every action there is an equal and opposite standard sea level temperature is. reaction. A. 29°C. Page B. Force is proportional to the product of mass and B. 59°F. acceleration. C. 59°C. DOWNLOAD OUR MOBILE APP FROM PLAY STORE @DGCA QUESTION PAPERS IF YOU HAVE PREVIOUS SESSION QUESTION PAPERS, SHARE WITH US AT [email protected]  WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material 15.1 Fundamentals 15.2 Engine Performance 15.3 Inlet Ans.- 59°F. Ans.- turbine. Explanation. NIL. Explanation. Jeppesen Aircraft Powerplant Page 2- 9. 4(www.dgcaquestionpapers.in), Like us on Facebook @ fb/DGCAQuestionPapers ( All CAR 66 Module Exam QP Available Q. 33. Standard sea level pressure is. A. 29.92 inches Hg. Q. 39. A modular constructed gas turbine engine B. 29.29 inches Hg. means that. C. 29.00 inches Hg. A. all engines have a specific component layout. Ans.- 29.92 inches Hg. B. the engine is constructed by the vertical assembly Explanation. NIL. technique. C. its major components can be removed and replaced without disturbing the rest of the engine. Q. 34. The highest pressure in a gas turbine is. Ans.- its major components can be removed and replaced without disturbing the rest of the engine. A. at the nozzle exit. Explanation. The Dictionary of Aircraft Terms by B. at the burner exit. Dale Crane has this definition. C. just after the last compressor stage but before the burner. Ans.- just after the last compressor stage but before the Q. 40. The accessory gearbox of a high bypass engine burner. is. Explanation. Rolls Royce The Jet Engine Page 15 A. on the HP Compressor housing. refers. B. in the forward bearing housing. C. attached to the turbine casing. Ans.- on the HP Compressor housing. Q. 35. The velocity of subsonic air as it flows through Explanation. Jeppesen Aircraft Powerplant Page 3- a convergent nozzle. 9. A. remains constant. B. increases. C. decreases. Q. 41. On a gas turbine engine, what is the fan driven Ans.- increases. by?. Explanation. NIL. A. I P turbine. B. LP turbine. C. H P turbine. Q. 36. A turboprop engine derives its thrust by. Ans.- LP turbine. Explanation. Rolls Royce The Jet Engine Page 6 A. impingement of the prop-wash on the outside air. refers. B. reaction of the prop-wash. C. reaction of the propulsion gases. Ans.- reaction of the prop-wash. Q. 42. Which law relates to the kinetic, pressure, and Explanation. Newtons Third Law. potential energy in a fluid flow?. A. Bernoulli's theorem. Q. 37. Adiabatic compression is. B. Newton's laws. A. an isothermal process. C. Charles's law. B. one where there is an increase in kinetic energy. Ans.- Bernoulli's theorem. C. one where there is no loss or gain of heat. Explanation. The sum of the energies in a system is Ans.- one where there is no loss or gain of heat. constant. so if one decreases another will increase. Explanation. Sherwin and Horsley Thermodynamics Page 144 refers. Q. 43. The density of gas may be expressed as. Q. 38. In a ducted fan engine, the fan is driven by the. A. volume/weight. B. weight/volume. A. turbine. C. pressure/volume. Page B. air passing over the compressor. Ans.- weight/volume. C. accessory gearbox. Explanation. Basic Physics this one. DOWNLOAD OUR MOBILE APP FROM PLAY STORE @DGCA QUESTION PAPERS IF YOU HAVE PREVIOUS SESSION QUESTION PAPERS, SHARE WITH US AT [email protected]  WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material 15.1 Fundamentals 15.2 Engine Performance 15.3 Inlet A. the increase of dynamic pressure at the face of the compressor. Q. 44. E S HP is. B. conversion of static pressure to kinetic pressure at 5(www.dgcaquestionpapers.in), Like us on Facebook @ fb/DGCAQuestionPapers ( All CAR 66 Module Exam QP Available A. Horsepower/efficiency. the face of the compressor. B. Shaft horse power + exhaust efflux. C. conversion of kinetic energy to pressure energy at C. Power available at the turbine less the power the face of the compressor. required to drive the. Ans.- conversion of kinetic energy to pressure energy at Ans.- Shaft horse power + exhaust efflux. the face of the compressor. Explanation. Effective Shaft Horse Power is the Explanation. The greater the ram effect the greater measure of total power of a turbo prop engine. the efficiency of the propulsion system. Q. 45. A divergent duct will cause subsonic flow to Q. 50. Which of the following statements is true on a decrease in. high bypass ratio A. velocity, increase pressure. turbofan?. B. velocity, pressure remains constant. A. Both the compressor and combustion system are C. pressure, increase velocity. larger than their turbojet equivalent. Ans.- velocity, increase pressure. B. The compressor assembly is larger and combustion Explanation. Rolls Royce The Jet Engine page 13 fig chamber smaller than their turbojet equivalent. 2-3 refers. C. Both the compressor and combustion chamber are smaller than the turbojet equivalent. Ans.- Both the compressor and combustion chamber Q. 46. The Brayton cycle is. are smaller than their turbojet equivalent. A. the name given to the intermittent cycling of an Explanation. Smaller compressors and combustion electrical de-icing system. chambers can be used on high bypass fans as they are B. the continuous combustion cycle taking place in a gas more efficient than turbo jets. turbine engine. C. the constant velocity cycle taking place in a gas turbine engine. Q. 51. In the dual axial flow or twin spool compressor Ans.- the continuous combustion cycle taking place in a system with a free power turbine, Nf would be an gas turbine engine. indication of. Explanation. The Brayton Cycle is also known as the A. turbine thrust indication. constant pressure cycle. B. first stage compressor speed. C. free power turbine speed. Ans.- free power turbine speed. Q. 47. The purpose of a diffuser is to. Explanation. The free turbine drives the prop-shaft A. increase the kinetic energy of the air. only. B. induce a swirl to the air prior to combustion. C. increase the static pressure of the air. Ans.- increase the static pressure of the air. Q. 52. A waisted drive shaft is primarily to. Explanation. Diffusers are always static divergent ducts. A. achieve dynamic balance. B. reduce weight. C. provide a fuse if the driven component is overloaded. Q. 48. On a triple spool engine, the first stage of turbines drive. Ans.- provide a fuse if the driven component is A. the LP compressor. overloaded. B. the HP compressor. Explanation. An example of this type of drive shaft C. the I P compressor. is fitted between a gearbox and an I D G. Ans.- the HP compressor. Explanation. Rolls Royce The Jet Engine Fig 2-5-2 refers. Q. 53. The 'core engine' or 'gas generator' is made up of the following components:. A. Inlet, compressor, combustion chamber, turbine, Page Q. 49. Ram effect is. exhaust. B. Turbine, combustion chamber, compressor. DOWNLOAD OUR MOBILE APP FROM PLAY STORE @DGCA QUESTION PAPERS IF YOU HAVE PREVIOUS SESSION QUESTION PAPERS, SHARE WITH US AT [email protected]  WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material 15.1 Fundamentals 15.2 Engine Performance 15.3 Inlet C. Compressor, turbine, exhaust, propelling nozzle. Q. 2. The efficiency of a gas turbine engine at Ans.- Turbine, combustion chamber, compressor. altitude. Explanation. The core engine is that which the A. decreases. 6(www.dgcaquestionpapers.in), Like us on Facebook @ fb/DGCAQuestionPapers ( All CAR 66 Module Exam QP Available primary airflow passes(the air that passes through the B. remains constant. combustion chamber.The inlet is not included as the air C. increases. is normally split down the bypass duct at the entrance Ans.- increases. to the compressor system. Explanation. The compressor performs better at lower air temperatures(see Jeppersen Gas Turbines Page 2-33) thus improving thermal efficiency. Also Q. 54. The principle of jet propulsion is. lower air temperatures up to the tropopause assist in A. the calorific value of fuel burnt is equal to aircraft. maintaining Propulsive Efficiency(whilst accepting that B. the interaction of fluids and gases. decreasing density decreases mass flow). Also note that C. every action has a equal and opposite reaction. operators fly at the tropopause whenever possible even Ans.- every action has a equal and opposite reaction. for short flights for the best SFC. Explanation. This is Newtons Third Law. Q. 3. Which statement is true regarding jet engines?. Q. 55. Boyle's law states that, at constant temperature, if a gas is compressed. A. At the higher engine speeds, thrust increases rapidly A. its absolute pressure is proportional to its volume. with small increases in RPM. B. its absolute temperature is proportional to it's B. At the lower engine speeds, thrust increases rapidly volume. with small increases in RPM. C. its absolute pressure is inversely proportional to its C. The thrust delivered per pound of air consumed is volume. less at high altitude. Ans.- its absolute pressure is inversely proportional to Ans.- At the higher engine speeds, thrust increases its volume. rapidly with small increases in RPM. Explanation. If the volume is reduced the pressure Explanation. Jeppesen A&P Powerplant Textbook goes up. 3-43. Q. 56. What part of a jet engine has the most Q. 4. Some turboprop and turbojet engines are potential energy?. equipped with two spool or split compressors. When A. Immediately after the combustion chamber. these engines are operated at high altitudes, the. B. Just before the combustion chamber. C. Immediately after the HP compressor. A. low pressure rotor will increase in speed as the Ans.- Just before the combustion chamber. compressor load decreases in the lower density air. Explanation. Where the fuel (unburned) is pumped B. low pressure rotor will decrease in speed as the in. compressor load decreases in the lower density air. C. throttle must be retarded to prevent overspeeding of the high pressure rotor due to the lower density air. Ans.- low pressure rotor will increase in speed as the 15.2 Engine Performance. compressor load decreases in the lower density air. Explanation. Jeppesen A&P Powerplant Textbook 3-18. Q. 1. Ram effect' due to aircraft forward speed will cause the efficiency of the engine to. Q. 5. Ram effect' due to aircraft forward speed will A. remain constant. cause the thrust of the engine to. B. decrease. A. remain constant. C. increase. B. decrease. Ans.- increase. C. increase. Explanation. Ram effect improves compression Ans.- remain constant. ratio which improves thrust without using extra fuel Explanation. Thrust is constant, but efficiency will Rolls Royce The Jet engine Page 219 refers. increase. Page DOWNLOAD OUR MOBILE APP FROM PLAY STORE @DGCA QUESTION PAPERS IF YOU HAVE PREVIOUS SESSION QUESTION PAPERS, SHARE WITH US AT [email protected]  WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material 15.1 Fundamentals 15.2 Engine Performance 15.3 Inlet Q. 6. With a fixed throttle, and with increased A. Compressor inlet air temperature. massairflow, what happens to EPR?. B. Burner can pressure. A. EPR goes up. C. Turbine inlet temperature. 7(www.dgcaquestionpapers.in), Like us on Facebook @ fb/DGCAQuestionPapers ( All CAR 66 Module Exam QP Available B. EPR remains constant. Ans.- Turbine inlet temperature. C. EPR goes down. Explanation. NIL. Ans.- EPR goes down. Explanation. With increasing mass airflow with throttles fixed Ram pressure (Pt2) increases but the P7 Q. 12. At altitude, idling RPM is. pressure remains the same. Jeppesen Aircraft Gas A. same as at sea level. Turbines page 12-18 refers. B. higher than at sea level. C. lower than at sea level. Ans.- higher than at sea level. Q. 7. At what stage in a gas turbine engine are gas Explanation. Due to decreased density there is less pressures the greatest? resistance to rotation. A. Compressor outlet. B. Turbine outlet. C. Compressor inlet. Q. 13. Thrust. Ans.- Compressor outlet. A. increases with high temperature. Explanation. NIL. B. increases with low temperature. C. decreases with low temperature. Ans.- increases with low temperature. Q. 8. Increasing ram effect with increased speed. Explanation. Jeppesen Gas Turbine Powerplants Page 2-33 Refers. A. reduces thrust due to reduced compressor efficiency. B. increases thrust due to increased maximum airflow. Q. 14. Which of the following variables affect the inlet air density of a turbine engine?. C. reduces thrust due to reduced turbine temperature. A. Altitude of the aircraft, Ambient temperature. B. Compression ratio, Turbine inlet temperature, Ans.- increases thrust due to increased maximum Altitude of the aircraft, Ambient temperature. airflow. C. Speed of the aircraft, Compression ratio, Turbine inlet Explanation. Jepperson Gas Turbine Powerplants temperature,Altitude of the aircraft. Page 2-35 refers. Ans.- Altitude of the aircraft, Ambient temperature. Explanation. NIL. Q. 9. The highest heat to metal contact in a jet engine is the. Q. 15. The propulsive efficiency is. A. burner cans. A. low, with a low mass flow acceleration. B. turbine inlet guide vanes. B. high, with a low mass flow acceleration. C. turbine blades. C. high, with a high mass flow acceleration. Ans.- turbine inlet guide vanes. Ans.- high, with a low mass flow acceleration. Explanation. NIL. Explanation. Jeppesen Gas Turbine Powerplants Page 2-37 Refers - a large mass of air moved slowly!. Q. 10. Which compressor type gives the greatest advantages for both starting flexibility and improved Q. 16. The RPM for maximum power would be. high altitude performance?. A. Single spool, axial flow. A. lower on a colder day. B. Dual stage, centrifugal flow. B. lower on a hotter day. C. Split spool, axial flow. C. greater on a colder day. Ans.- Split spool, axial flow. Ans.- lower on a colder day. Explanation. NIL. Explanation. Jeppesen Gas Turbine Powerplant Page 3-16 refers. Page Q. 11. Which of the following is the ultimate limiting factor of turbine engine operation?. DOWNLOAD OUR MOBILE APP FROM PLAY STORE @DGCA QUESTION PAPERS IF YOU HAVE PREVIOUS SESSION QUESTION PAPERS, SHARE WITH US AT [email protected]  WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material 15.1 Fundamentals 15.2 Engine Performance 15.3 Inlet Q. 17. How does engine thrust vary with B. is minimum. temperature?. C. is maximum. A. Increase in temperature gives greater thrust because Ans.- is minimum. 8(www.dgcaquestionpapers.in), Like us on Facebook @ fb/DGCAQuestionPapers ( All CAR 66 Module Exam QP Available of low friction in compressors. Explanation. Jeppesen Gas Turbine Powerplants B. Low temperatures give low thrust. Page 2-29 refers. C. Low temperature gives greater mass flow and therefore greater thrust. Ans.- Low temperature gives greater mass flow and Q. 23. The efficiency of conversion of kinetic energy therefore greater thrust. into propulsive work is a measure of. Explanation. Jeppesen Aircraft Gas Turbine Power A. mechanical efficiency. plant Page 2-33 Refers. B. propulsive efficiency. C. thermal efficiency. Ans.- propulsive efficiency. Q. 18. A method of comparing engine efficiencies is Explanation. Jeppesen Gas Turbine Powerplants by comparing. Page 2-29 refers. A. fuel consumption. B. thrust to weight ratio. C. specific fuel consumption. Q. 24. What effect does high atmospheric humidity Ans.- specific fuel consumption. have on the operation of a jet engine?. Explanation. Jeppesen Aircraft Gas Turbine Power A. Decreases compressor and turbine RPM. plant Page7-3 Refers. B. Decreases engine pressure ratio. C. Has little or no effect. Ans.- Has little or no effect. Q. 19. With a fixed throttle in a climb. Explanation. Jeppesen A&P Technician Propulsion A. RPM will increase. Textbook 7-70. B. RPM will remain constant. C. RPM will decrease. Ans.- RPM will increase. Q. 25. Power is adjusted in a gas turbine engine by. Explanation. Jeppesen Gas Turbine Powerplants Page 3-15 refers. A. increasing fuel flow. B. increasing air and fuel flow. C. increasing airflow to the combustion chamber. Q. 20. The point of maximum velocity in the engine is Ans.- increasing air and fuel flow. in the. Explanation. You cannot have extra fuel without A. exhaust exit nozzle. extra air. B. combustion chamber. C. nozzle guide vanes. Ans.- exhaust exit nozzle. Q. 26. The engine rating plug. Explanation. Rolls Royce The Jet Engine page 15 A. is permanently connected to the E E C. refers. B. is connected to the EPR transmitter. C. is permanently connected to the Engine casing. Ans.- is permanently connected to the Engine casing. Q. 21. At constant RPM, the pressure ratio of the Explanation. Jeppesen Aircraft Powerplant Page 7- compressor and the temperature rise across the 21. compressor. A. increases with height. B. remains constant irrespective of height. Q. 27. Flat Rated thrust is defined as. C. decrease with height. A. the thrust at the ambient temperature point above Ans.- remains constant irrespective of height. which thrust drops below 100%. Explanation. Jeppesen Aircraft Gas Turbine B. that power achieved at idle RPM. Powerplant Page 3-20 refers. C. that power achieved at maximum EGT. Ans.- the thrust at the ambient temperature point above which thrust drops below 100%. Q. 22. With the aircraft stationary, propulsive Explanation. Jeppesen Aircraft Powerplant Page 7- Page efficiency. 34. A. depends on RPM. DOWNLOAD OUR MOBILE APP FROM PLAY STORE @DGCA QUESTION PAPERS IF YOU HAVE PREVIOUS SESSION QUESTION PAPERS, SHARE WITH US AT [email protected]  WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material 15.1 Fundamentals 15.2 Engine Performance 15.3 Inlet Ans.- maximum turbine temperature. Q. 28. Thrust rating on an FADEC controlled engine Explanation. The turbine is the most highly stressed can be changed by. component in the engine. 9(www.dgcaquestionpapers.in), Like us on Facebook @ fb/DGCAQuestionPapers ( All CAR 66 Module Exam QP Available A. varying the ballast resistor in the EGT system. B. changing the engine rating plug. C. varying the EPR datum plug. Q. 34. To ensure an engine maintains self sustaining Ans.- changing the engine rating plug. speed. Explanation. Jeppesen Aircraft Powerplant Page 7- A. idle remains same for any density. 21 refers. B. idle increases with density decrease. C. idle increases with density increase. Ans.- idle increases with density decrease. Q. 29. Propeller torque is analogous to. Explanation. Rolls Royce The Jet Engine page 103 A. engine RPM. para 15 refers. B. shaft horsepower. C. propeller RPM. Ans.- shaft horsepower. Q. 35. A factor that limits EGT is the. Explanation. Propeller torque is equal and opposite A. jet pipe. to SHP under steady state conditions. B. compressors. C. turbine. Ans.- turbine. Q. 30. The total power in a turboprop engine is the. Explanation. Rolls Royce the Jet Engine Page 13 refers. A. SHP. B. BHP. C. E S HP. Q. 36. Thrust will. Ans.- E S HP. A. increase at high temperatures. Explanation. E S HP = shaft horse power plus B. decrease at low temperatures. residual gas exhaust thrust. C. increase at low temperatures. Ans.- increase at low temperatures. Explanation. Higher density gives higher mass flow Q. 31. In a dive, with the throttles fixed, the EPR will. hence higher thrust. A. not change. B. increase. Q. 37. Across the turbines, there is. C. decrease. A. a general temperature rise. Ans.- decrease. B. a general temperature drop. Explanation. Jeppesen Aircraft Gas Turbines page C. an isometric expansion. 12-18 refers. Ans.- a general temperature drop. Explanation. Rolls Royce the Jet Engine Page 15 shows a temperature decrease across the turbines due Q. 32. With an increase in forward speed, the engine to energy extraction. thrust. A. decreases slightly but recover due to ram effect. B. increases. Q. 38. If the throttle position remains constant. C. decreases. Ans.- decreases slightly but recover due to ram effect. A. with increasing OAT, RPM and TGT will increase. B. with decreasing OAT, RPM will increase. Explanation. Jeppesen Aircraft Gas Turbine C. with increasing OAT, TGT will increase. Powerplant Page 2-35 refers. Ans.- with increasing OAT, RPM and TGT will increase. Explanation. As OAT increases the air is thinner Q. 33. The main factor considered when designing an RPM increases but thrust decreases due to the thin air. engine is. Extra fuel is required to increase thrust therefore TGT A. maximum fuel consumption. increases. Page B. maximum turbine temperature. C. maximum tip speed. DOWNLOAD OUR MOBILE APP FROM PLAY STORE @DGCA QUESTION PAPERS IF YOU HAVE PREVIOUS SESSION QUESTION PAPERS, SHARE WITH US AT [email protected]  WWW.EASAQUESTIONPAPERS.BLOGSPOT.COM PART -66 MODULE 15 PART 1 Visit to download all latest EASA / DGCA CAR 66 Module examination Question papers and study material 15.1 Fundamentals 15.2 Engine Performance 15.3 Inlet Q. 39. If an aircraft climbs with a fixed throttle position. 10(www.dgcaquestionpapers.in), Like us on Facebook @ fb/DGCAQuestionPapers ( All CAR 66 Module Exam QP Available A. thrust decreases and RPM increases. Q. 44. To maintain the selected RPM of a gas turbine B. thrust and RPM remain the same. at altitude. C. thrust increases and RPM remains the same. A. the pilot will have to throttle back. Ans.- thrust decreases and RPM increases. B. more fuel will automatically be added. Explanation. Thinner air causes thrust to decrease C. the fuel will automatically be reduced as the aircraft and the compressor to speed up. climbs. Ans.- the fuel will automatically be reduced as the aircraft climbs. Q. 40. Ram pressure recovery will generally take Explanation. In a hydro mechanical engine the P1 effect at aircraft speeds of. capsule will sense increasing altitude and trim off the