Module17 New.doc

Module 17, Propeller.17.1. Fundamentals. Question Number. 1. High speed propellers are designed to. Option A. rotate at high RPM. Option B. operate at high forward speeds. Option C. operate at supersonic tip speeds. Correct Answer is. operate at high forward speeds. Explanation. NIL. Question Number. 2. When in the windmill position ATM. Option A. opposes CTM. Option B. is not related to CTM. Option C. assists CTM. Correct Answer is. assists CTM. Explanation. ATM normally increases blade angle but in the windmill condition reverses and assists CTM. Question Number. 3. The optimum angle for a fixed pitch propeller is. Option A. 15 degrees. Option B. 2 - 4 degrees. Option C. 6 - 10 degrees. Correct Answer is. 2 - 4 degrees. Explanation. Jepperson A&P Powerplant Page 12-4 Refers. Question Number. 4. A left handed propeller is one that. Option A. rotates clockwise when viewed from the rear. Option B. rotates clockwise when viewed from the front. Option C. is fitted to an engine on the left side of the aircraft. Correct Answer is. rotates clockwise when viewed from the front. Explanation. Left hand propeller rotates anti-clockwise when viewed from the rear. http://www.baypropeller.com/parts.html Question Number. 5. Forces acting on a propeller are. Option A. centrifugal, twisting, and bending. Option B. torque, thrust and centrifugal. Option C. torsion, tension and thrust. Correct Answer is. centrifugal, twisting, and bending. Explanation. Jepperson Powerplant Page 12-5 to 12-7 refers. Question Number. 6. The blade angle at the root is. Option A. less than the tip. Option B. same from tip to root. Option C. greater than the tip. Correct Answer is. greater than the tip. Explanation. Jepperson Aircraft Propellers and Controls Page 13 Refers. Question Number. 7. What force on a propeller blade turns the blades to a fine pitch?. Option A. ATM. Option B. Torque. Option C. CTM. Correct Answer is. CTM. Explanation. Jepperson Aircraft Propellers and Controls Page 15 refers. Question Number. 8. The purpose of propeller twist is. Option A. coarsen the blade angle at the root. Option B. to maintain Blade Angle along the blade. Option C. to maintain Angle of Attack at the same value along the blade. Correct Answer is. to maintain Angle of Attack at the same value along the blade. Explanation. Jepperson Aircraft Propellers and Controls Page 13 Refers. Question Number. 9. The forces acting on a propeller blade are. Option A. bending, twisting and centrifugal. Option B. thrust, aerodynamic and tension. Option C. thrust and torque. Correct Answer is. bending, twisting and centrifugal. Explanation. Refer Jepperson Powerplant Page 12- 5 to 7. Question Number. 10. Blade angle at the root is. Option A. low. Option B. high. Option C. master blade angle. Correct Answer is. high. Explanation. Jepperson Aircraft Propellers and Control Pages 55-58 Refer. Question Number. 11. Blade angle is taken from the chord and. Option A. propeller shaft. Option B. relative airflow. Option C. plane of rotation. Correct Answer is. plane of rotation. Explanation. Jepperson Aircraft Propellers and Control Page132 refer. Question Number. 12. What forces act on a propeller blade?. Option A. Thrust and torque. Option B. Bending, thrust, torque. Option C. Bending, CTM and ATM. Correct Answer is. Bending, CTM and ATM. Explanation. Refer Jepperson Aircraft Propellers and Controls Page 14-15 Note Thrust and Torque are both. Question Number. 13. CTM will. Option A. try to bend the blade away from the engine. Option B. turn the blade about the lateral axis. Option C. cause the tips to rotate at supersonic speeds. Correct Answer is. turn the blade about the lateral axis. Explanation. Jepperson Aircraft Propellers and Controls page Page 15 refers. Question Number. 14. From reverse pitch, to return to normal pitch it. Option A. passes through coarse then fine. Option B. passes through coarse. Option C. passes through fine. Correct Answer is. passes through fine. Explanation. NIL. Question Number. 15. When in reverse pitch, CTM will tend to move the propeller blades towards. Option A. a positive pitch. Option B. a position depending on rpm. Option C. a negative pitch. Correct Answer is. a positive pitch. Explanation. CTM always rotates towards the plane of rotation. Correct Answer is. If the blade angle is increased. the ratio of the useful work done by the propeller to work done by the engine on the propeller. Option B. A rotating propeller imparts rearwards motion to a. Propeller efficiency is. Jepperson A & P Powerplant Page 12-6. Option A. large mass of air at low velocity. Option A. Question Number. Question Number. small mass of air at low velocity. Option C. . forces are produced. 19. thrust and torque. Explanation. Option C. Correct Answer is. the ratio of the work applied to the geometric pitch to useful work on the C. Option B. the pitch becomes finer. 18. Correct Answer is. lateral stability decreases. Option A. Explanation. As a propeller blade moves through the air. Option C. 16. Option B. small mass of air at high velocity. 17. Correct Answer is. which are known as. Option C. the pitch becomes coarser. Kermode Mechanics of Flight Fig 4. Explanation.U.4 refers. the ratio of output speed to input propeller speed. large mass of air at low velocity. lift and drag. Question Number. the pitch becomes coarser. the ratio of the useful work done by the propeller to work done by the engine on the propeller.S. lift and torque. thrust and torque. Pitch is an alternative name for blade angle. Option B. Option A.Question Number. rotation. 21. Option A. changing pitch. Question Number. Option C. Option B. rotation. in one revolution. in one revolution when slip is maximum. 20. range. Option A. Option C. Jepperson Aircraft Propellers and Controls page 15. Question Number. decrease. Explanation. increase. Correct Answer is. Explanation. . Option B. Geometric Pitch is the distance moved. 22. Jepperson A&P Powerplant Page 12-4 refers. Option A. The angle between the resultant airflow direction and the propeller blade plane of rotation is known as. Explanation. Option C. Option A. CTM increases as a function of Centrifugal. 23. Correct Answer is.p. Correct Answer is.m. Option B. blade angle. angle of attack. feathering. As propeller rotation speed increases the centrifugal turning moment on the blades will. increase. Jepperson Aircraft Propellers and Controls page 15 refers. remain constant through r. Question Number. in one revolution without slip. Question Number. Kermode Mechanics of Flight Page 134 Refers. Option B. in one revolution without slip.Explanation. Propeller torque is the resistance offered by the propeller to. Option C. turns the blades to high pitch. Propeller blade angle. Question Number. Correct Answer is. take off and climb. Correct Answer is. . 28. maximum economical cruise in level flight. maximum economical cruise in level flight. is constant along the blade length. forward speed. 27 . increases from root to tip. Explanation. Correct Answer is. Option B. Jepperson Aircraft Propellers and Controls Fig 11-33 refers. Option A. decreases from root to tip. Option A. At constant rpm. Coarse pitch is used for. Explanation. Aerodynamic Twisting Moment. Explanation. Correct Answer is. The helix angle is the angle between the plane of rotation and the relative airflow. Jepperson A&P Powerplant Fig 12-8 refers Question Number. Option B. root. SHP. Jepperson Aircraft Propellers and Controls page 30 refers. Explanation. Option A. forward speed. landing and power checks. Correct Answer is. Jepperson A&P Powerplant Fig 12-12 refers. Explanation. 25 . Option A. Under normal operation the point of maximum stress on a propeller blade is at the. 24. advance per revolution depends on. Explanation. Correct Answer is. Option B. Option C. turns the blade to windmill. Option C. helix angle or angle of advance. root. 26 . Question Number. Option A. helix angle or angle of advance. Option B. decreases from root to tip. Jepperson A&P Powerplant Page 12/6 refers. Question Number. turns the blades to high pitch. Question Number. geometric pitch plus slip. Windmilling causes. Torque acts. Question Number. Question Number. Option A. pitch measured at the master station. maximum propeller drag. Option A. Windmilling occurs with a small negative AoA and a small positive blade angle. Correct Answer is. Correct Answer is. Option B. Option B. Correct Answer is. Option A. Question Number. 29. Explanation. Effective pitch is. a small positive angle of attack. Option C. Centrifugal Twisting Moment. propeller underspeeding. a small negative angle of attack. in the same direction as the plane of rotation. Option C. Explanation. distance moved in one revolution. 32. A windmilling Propeller has.Question Number. at right angles to the plane of rotation. in opposition to the direction of rotation. distance moved in one revolution. Correct Answer is. Option A. Explanation. . Effective pitch is geometric pitch minus slip. NIL. 30. Option C. Option B. a small positive blade angle. maximum propeller drag. in opposition to the direction of rotation. Option C. a small negative angle of attack. 31. Option B. about the twisting axis. bending forward. Option B. Option B. 36. 33. Option A. at 70 to 80% of propeller length. Option C. in the first 50%. to even out thrust distribution across the propeller. less. 34. Option A. Beyond this point the blade chord is reduced to lessen tip thrust. reduce angle of attack at the blade root. Question Number. the same all along the length. Jepperson Aircraft Propellers and Controls Page 14 refers. Option C. at 70 to 80% of propeller length. 35. Correct Answer is. Option B. Option A. Correct Answer is. Explanation. to even out thrust distribution across the propeller. Option C. Explanation. Question Number. Question Number. about its twisting axis. The velocity of the slipstream behind the aircraft in relation to the ambient air is. Explanation. Option A. about its twisting axis. CTM changes the pitch of a blade. Option B. to ensure that tip speed does not go faster than Mach 1. CTM reduces pitch towards the plane of rotation. . Correct Answer is. Jepperson Aircraft Propellers and Controls Page 15 refers. Question Number. equal. Option C. towards the feather plane. greater. The purpose of blade twist is to. Thrust is greatest.Explanation. highest. Given that blade angle is measured from the centre of the hub. is always fitted to the starboard engine. A right hand propeller. Left or right is determined by sitting in the cockpit and viewing the rotation. Option B. Question Number. Question Number. Option C. more drag in feather. Option A. 38. Option B.Correct Answer is. . 39. Option A. the tips. On helicopters they are called BERP tips. Explanation. rotates clockwise when viewed from the rear. highest. the blade angle at the hub is considered to be. Question Number. Correct Answer is. Option C. 40. T = mass ( Vout-Vin). Option A. Option A. Explanation. Question Number. Refer to Jeppesen Aircraft Propellers and controls page 13. Correct Answer is. A windmilling propeller will create. greater. Explanation. Option B. the tips. Master Station value. If there was not a difference then no thrust would be produced. the root. rotates clockwise when viewed from the rear. 37. Explanation. High speed aerofoils are employed at. Option C. the master station. Correct Answer is. rotates clockwise when viewed from the front. lowest. Option C. Option B. Option C. Explanation. Option C. NIL. 44. Option B. Question Number. a line joining the leading and trailing edges. a line joining the tip to the root of the blade. Explanation. intensifies the centrifugal forces to some degrees.Option B. Option A. Question Number. a line joining the tips of the blades. Option C. more drag in fine pitch. Correct Answer is. 42. Thrust bending force on a propeller blade. Question Number. can be used in propeller design to reduce some operation stress. the plane in which thrust force acts. A windmilling propeller is always in fine pitch. Explanation. 43. Option B. Option A. NIL. Correct Answer is. the angle at which the blade strikes the airflow. . NIL. the plane in which the propeller rotates. more drag in coarse pitch. 41. tends to bend the propeller blade forward at the tip. The plane of rotation is defined as. more drag in fine pitch. Option A. What conditions are applied to a propeller blade windmilling?. The chord line of a propeller is. the plane in which the propeller rotates. a line joining the leading and trailing edges. Correct Answer is. Question Number. Explanation. tends to bend the propeller blade forward at the tip. Correct Answer is. NIL. 1. Option B. Positive angle of attack. create lift on the fixed aerofoils of an aircraft. Propeller Construction. change engine horsepower to thrust. Option C. NIL. thrust negative. Negative angle of attack. NIL. 45. Option C. Option A. Option B. Question Number.Option A. Question Number. eliminate the drag created by a windmilling propeller when an engine fails in flight. Negative angle of attack. . A fibreglass composite blade. Option C. will never be struck by lighting. does not require lightning strike protection. thrust negative. Question Number.2. Correct Answer is. 17. Explanation. Option A. prevent further engine damage when an engine fails in flight. The primary purpose of propeller is to. Negative angle of attack. Correct Answer is. eliminate the drag created by a windmilling propeller when an engine fails in flight. Option B. prevent propeller damage when an engine fails in flight. thrust negative. Explanation. change engine horsepower to thrust. 46. Option A. provide static and dynamic stability to aircraft. Option B. requires lightning strike protection. thrust positive. The primary purpose of a feathering propeller is to. Option C. Explanation. Correct Answer is. Explanation. Explanation. . Option C. strain gauges in the reduction gear. NIL. Option A. NIL. Option B. stress gauges in the reduction gear. for balancing. Question Number. Option C. Option A. Question Number. strain gauges in the reduction gear. Option B. 5. hydraulic oil as the pressure medium. engine oil as the pressure medium. pressure transducers in the reduction gear. requires lightning strike protection. Electronic torque measuring systems utilise. Option A. Correct Answer is. birch. Question Number. birch. The timber most often used today for propeller construction is. Explanation. Explanation. Pallett Aircraft Instruments and integrated Systems page 357. spruce. Metal at the tip and along the leading edge of a wooden propeller is. Question Number. balsa. Option B. A conventional turboprop torque meter uses. engine oil as the pressure medium. coiled spring levers as the pressure medium. 4.Correct Answer is. Option A. Correct Answer is. 2. Correct Answer is. NIL. for protection. 3. Option C. Option B. . The minimum percentage seating on a propeller rear cone should be. Option B. Option A. Correct Answer is. initiate auto-feather. Jepperson Aircraft Propellers and Controls page 135 Refers. Explanation. Option A. Explanation. Correct Answer is. Blade cuffs are fitted to the root of the blades. Option C. Explanation. Correct Answer is. increase pitch. Explanation. Refer Jepperson Aircraft Propellers and Controls Page 135. Correct Answer is. Refer Jepperson Powerplant Page 12. 7. increase power. reduce drag following engine shutdown. Option A. 9. Low torque sensing is used to. Option C. Option B. Question Number. to increase the strength of the blade. to increase thrust. initiate auto-feather. Option B. reduce drag. Question Number. for Anti-icing. 90%.Option C. Jepperson Aircraft Propellers and Control page 18 refers. for protection. to increase flow of cooling air into the engine nacelle. Torque sensing is used to.3. 6. Option A. synchronise blade angle. Question Number. Question Number. Option C. reduce drag following engine shutdown. to increase flow of cooling air into the engine nacelle. 8. What does the torquemeter reading indicate in a gas turbine engine?. 90° to plane of rotation. 13. Jepperson Aircraft Propellers and Controls Page 31 shows 70% Old CAIPs shows 80%. Explanation. Explanation. Option B. Explanation. Correct Answer is. . Option C. 70%. Question Number. Compounded twin spool. The propeller is 'feathered' when the blades are at. Option C. The thrust of a propeller is normally taken by the. Jepperson A&P Powerplant Page 1-30/1-31 refers. Option C. 20° to plane of rotation. Explanation. Option A. front bearing in the reduction gear. Correct Answer is. Free turbine. Option B.Option B. torque meter. Option B. 0° to plane of rotation. Jepperson Aircraft Propellers and Controls page 75 refers. Question Number. 70%. Option A. 90° to plane of rotation. Direct coupled twin spool. Option A. Correct Answer is. 10. Question Number. front bearing in the reduction gear. 11. On which type of turbo-propeller would you expect to find a parking brake?. 12. Question Number. propeller rear cone. Option C. 95%. Correct Answer is. The parking brake stops the propeller rotating when the engine is stopped. Free turbine. Option B. Correct Answer is. 14. the rear pre-load shims.Jepperson Aircraft Propellers and Controls. The ratio between engine thrust and engine torque. Option C. Option B. moving cam. Option A. Reduction gearing allows the. Correct Answer is. Torque reaction at the reduction gear. Correct Answer is. Question Number. Option C. the front and rear cones. 15. Correct Answer is. blade tips to operate below the speed of sound. blade tips to operate above the speed of sound. Torque reaction at the reduction gear. Front and rear cones . Option B. 16. blade tips to rotate slower than the root of the propeller blade. the front and rear cones. Option C. Jepperson A&P Powerplant Page 12-16 refers. Engine torque. Question Number.Option A. Jepperson Aircraft Propellers and Controls Page 55 refers. The gear segments on the blade roots of a hydromatic propeller mesh with the. moving cam. Option A. stationary cam. Option B. torque tubes and eye bolts. Explanation. Question Number. Explanation. blade tips to operate below the speed of sound. Option A. the front git seal. A propeller is centralised on the propeller shaft by. Propellers always operate slower than the engine to ensure the blade tips do not go sonic. Explanation. Explanation. Option C. . Correct Answer is. Option C. Jepperson A&P Powerplant Fig 12-16 Refers. blade back or curved side. increasing blade thickness. Correct Answer is. Option C. Option B. Option A. 17. Question Number. Explanation. Explanation. Question Number. Option C. Option B. 18. Explanation. Drainage. Correct Answer is. Pivot points used during manufacture. 19. Drainage. Option B. Correct Answer is. Option B. Option A. increasing blade chord. ensure fully seated. Option A. When fitting a propeller to a tapered shaft. Jepperson Aircraft Propellers and Controls Page 143 refers.Question Number. blade face or flat side. What is the purpose of small holes at the tip of wooden propellers?. . Solidity of a propeller can be increased by. blade face or flat side. Explanation. locate the master spline. Option A. ensure the master spline and blade alignment are in accordance with the MM. Question Number. root to which the gear segment is fitted. Option C. The thrust face of a propeller blade is the. 20. increasing blade angle. locate the master spline. Balancing. Jepperson Aircraft Propellers and Controls Page 29 refers. AC Kermode Mechanics of Flight Page 138 refers. increasing blade chord. exhaust gas ingestion . Equivalent Shaft Horsepower (ESHP). . Explanation. Rolls Royce Jet Engine Page 5 refers. Correct Answer is. Explanation. Correct Answer is. high gas temperature and debris ingestion. Explanation. debris ingestion. Option A. Jepperson A&P Powerplant page 12-33 refers. Equivalent Shaft Horsepower (ESHP). Option A. Option B. Option A.Question Number. Shaft Horsepower (SHP). 24. Option C. A compound twin spool engine is. 23. ESHP is SHP plus residual thrust. Option B. Option C. Question Number. All large engines use Epicyclic reduction gearing. uses a spur gear reduction system. Option C. Option B. Option A. uses an epicyclic reduction gear system. debris ingestion. Question Number. turbo prop propeller driven by a power turbine. does not require a reduction gear system due to the propshaft being driven from the low speed compressor. high gas temperature. Option B. 22. Correct Answer is. uses an epicyclic reduction gear system. A turbo-prop engine. Option C. turbo prop twin spool compressor. LP Compressor driven by a free turbine. Question Number. turbo prop twin spool compressor. Correct Answer is. The disadvantage of using reverse pitch on a turbo-propeller engine is. 21. Brake Horsepower (BHP). Explanation. Total power of a turbo-prop engine is measured in. Option B. DTD 5 8 5. Option B. 25. Question Number. When the power lever on a turbo prop engine is moved from ground idle to flight fine the fuel flow increases and the blade angle. PCU oil pressure. Jepperson Aircraft Propellers and Controls Page 10 refers. Option B. How is the blade station measured?. 26. Option A.Question Number. Option A. increases. blade and spinner markings aligned. Correct Answer is. As a percentage of blade length from the tip. Explanation. flight fine pitch stop lever withdrawn. Question Number. 27. Option C. Option B. remains the same. Explanation. Option A. Option A. Ground idle is a lower pitch than flight idle. Option C. In inches from the centre of the hub. Question Number. In inches from the tip. Correct Answer is. . Unattributed notes. Correct Answer is. Option C. 28. With the engine stationary the indication that the propeller is in ground fine pitch is. In inches from the centre of the hub. Option C. Explanation. blade and spinner markings aligned. engine oil pressure boosted by a pump driven off the reduction gear. increases. decreases. The oil used in the torquemeter system is. below stop warning light on. Correct Answer is. Correct Answer is. One using a centrifugal compressor. Option A. during take off. Compound twin spool. There is only one gauge for all engines. Option B. With a multi-engined aircraft the torque pressure would be. Directly coupled. 31. during landing. Rolls Royce The Jet Engine page 5 refers. shank. Jepperson Aircraft Propellers and Controls Page 136 refers. in the cruise. Option B. in the cruise. Question Number. Jepperson Aircraft Propellers and Controls Page 13 refers. Option A.Correct Answer is. Blade stations are measured from the. Auto feathering is disarmed. . Compound twin spool. Question Number. Option C. Option A. Correct Answer is. Which type of turboprop engine is practically free from surge and requires low power for starting?. engine oil pressure boosted by a pump driven off the reduction gear. Explanation. Explanation. Option C. centre of the hub. 32. centre of the hub. Option B. Option C. 29. 30. Explanation. tip. Option A. Explanation. Question Number. Question Number. Rolls Royce The Jet Engine Fig 12-4 Refers. provide aerodynamic breaking. allow aircraft to taxi backwards. Question Number. Option C. Question Number. similar on all engines. Option A. TAS. Relative airflow is a function of rotational speed and TAS. 34. Explanation. Explanation. Engine would continue to run. TAS. Option C. 36. Question Number. Option C. Correct Answer is. but if it is just the gauge. Correct Answer is. Option C. A ducted propeller is used because. Correct Answer is. All engines are synchronised to the same RPM and are travelling at the same forward speed. Explanation. 35. then the engine would be unaffected. The RPM of a windmilling propeller is primarily related to. Engine would continue to run. Option B. IAS. 33. Explanation. Option A. EAS. Engine would overspeed. same on all engines. The purpose of using reverse pitch propellers is to. Option B. Auto feather would engage if torque had actually failed. same on all engines. reverse the direction of rotation of the propeller. Engine would auto feather. Option B. Jepperson aircraft propellers and controls Page 97 Refers. If torque pressure fell to zero during the cruise what would indicate that the gauge had failed?. Option A. Question Number. . provide aerodynamic breaking. Correct Answer is.Option B. Explanation. Explanation. only ducted propellers can be vectored. ducted props give more thrust for the diameter of disc. Option A. Option C. Question Number. Spring pressure + counterweights move it to coarse pitch. The duct provides for less tip losses. Option B. . ducted props give less thrust for the diameter of disc. boost engine oil pressure to alter pitch. high pitch for take off and low pitch for cruise. Question Number. ducted props give more thrust for the diameter of disc. Option C. low pitch for take off and climb and high pitch for cruise. boost engine oil pressure to increase pitch. maximum reverse pitch and Flight idle pitch. 37. low pitch for take off and climb and high pitch for cruise. 39. Jepperson aircraft propellers and controls Page 49 Refers. Question Number. A CSU is used on a single acting propeller system.Option A. coarse and flight fine pitch. Option B. Correct Answer is. Correct Answer is. Jeppesen Aircraft Propellers and controls page 108 refers. Option C. Explanation. Correct Answer is. Option A. Flight Idle and Ground Idle. boost engine oil pressure to decrease pitch. Explanation. Option B. A propeller operating in the Beta range is operating between. Option B. 38. maximum reverse pitch and Flight idle pitch. high pitch for take off. Option C. Correct Answer is. The CSU oil pump is provided to. low pitch for climb and descent and high pitch for cruise. Option A. A two position prop uses. boost engine oil pressure to decrease pitch. 43. Explanation. Option C. counter the ATM of the blades. the flat face. 42. Correct Answer is. Option B. a tractor propeller. Option A. the camber face. highest. They all mean the same. Question Number. balance the blades. Explanation. 41. Option B. Option C. Option B. Question Number. Explanation. 40. Option C. counteract the CTM of the blades. In blade station numbering the stations nearest the hub are. Option A.Question Number. a pusher propeller. Option A. counteract the CTM of the blades. Question Number. A tractor propeller pulls the aircraft through the air. Option A. . the leading edge. lowest. The counterweights are seen on single acting propeller systems. Blade stations are measured in inches-from the hub. Counterweights are used to. A propeller mounted forward of the engine is known as. Correct Answer is. Explanation. Option B. The pressure face of a propeller is. a tractor propeller. hydromatic propeller. datum. Correct Answer is. The pressure face is the thrust face or blade face. Option C. the flat face. lowest. Correct Answer is. Option C. Question Number. Explanation. Explanation. Question Number. reduction gear and propeller pitch chang mechanism. 46. reduction gear and propeller pitch chang mechanism. Option B. Option B. Correct Answer is. propellers on a twin engined aircraft revolving in opposite directions. the coarse pitch position to act as a brake. An aerodynamic braking propeller goes through. lower engine rpm. 47. . Option A. Turbo-prop engines require a slightly higher viscosity oil than a turbo-jet engine due to. 45. two propellers on the same shaft on one engine-each revolving in a different direction. The term spinner is applied to. Option B. Option A. Contra-rotating propellers are. Option A. You must go through fine to get to reverse. the feathered pitch position to act as a brake.Question Number. Explanation. Option C. The spinner covers the front of the hub. Correct Answer is. The mechanical gear system exerts higher forces on the lubricant. Question Number. the fine pitch position to act as a brake. Explanation. a streamline covering over the propeller hub. an acrobatic manoeuvre. a streamline covering over the propeller hub. Option A.the braking position. a propeller tip vortex. two propellers on the same shaft on one engine-each revolving in a different direction. higher engine rpm. propellers geared to rotate in the opposite direction to the engine. Option B. Correct Answer is. Enables extra power to be absorbed. Correct Answer is. 44. Option C. the fine pitch position to act as a brake. Option C. beta-range and reverse range. Option B. Option B. 48. 50. rich. cut-off. Variable pitch propellers are used because they are. 49. Explanation. Option A. . 51. Question Number. Question Number. within the range 450 mph and 700 mph. Option B.Question Number. Option A. Question Number. Turbo props are used only below 450 kts as the prop becomes inefficient above this. batch number. Option C. type certificate or equivalent certificate.905 refers. Correct Answer is. idle and high idle. Option C. reduce vibration and noise. below approximately 450 mph. Explanation. Option A. Option B. type certificate or equivalent certificate. above approximately 450 mph. lean and cut-off. Option C. range from 150-350 kts. Correct Answer is. The condition lever normally has the following settings. manufacturers data plate. JAR 25. have peak efficiency over a greater speed range. A propeller has the requirement of a. The propulsive efficiency of a propeller-turbine engine is higher than that of a jet-turbine engine at aircraft speeds. Option C. have peak efficiency over a greater speed range. normal. Correct Answer is. Option A. more economical. Explanation. below approximately 450 mph. Question Number. What is the ground clearance for a Tricycle Geared Aircraft?.Correct Answer is. Question Number. 54. Option C. Option B. more than 90°. Centrifugal latches are fitted to lock the propeller. cut-off. 1 inch. Correct Answer is. a decrease in propeller RPM will alter the angle of attack on the blade to. 55. idle and high idle. Jeppersen Aircraft Propellers and Controls Page 97 refers. To achieve reverse pitch the blade angle must be. Explanation. in the feathered position. 52. less than 0°. increase negative torque. 53. 9 inches. Option A. decrease angle of attack. Correct Answer is. Option A. Option B. decrease angle of attack. Correct Answer is. Option A. . increase angle of attack. more than 17°. Jeppersen A&P Powerplant page 12-36 refers. In a variable pitch propeller system. Explanation. Option A. less than 0°. 7 inches. Question Number. Explanation. the condition lever controls the propeller governor. Explanation. The blade fines off to maintain RPM. Option C. 7 inches. Option B. Jeppersen Aircraft Propellers and Controls Page 9 refers. Question Number. Option C. Option C. Question Number. Correct Answer is. Explanation. Option C. in the fine pitch position. coarse and fine pitch stops. 57. Explanation. Correct Answer is. coarse and fine pitch stops. cylinder. Question Number. . the feathering angle. blade root. counteract CTM. Option A. Option A. Correct Answer is. Option C. Option C. propeller shaft. Option B. Jeppersen Aircraft Propellers and Controls Page 71 refers. Used on lightweight single acting propeller systems.Option B. Option A. A Variable Pitch (VP) propeller will have at least 2 stops. 58. assist blade to move to fine pitch. although sophisticated types also have ground fine and reverse pitch stops. eppersen Aircraft Propellers and Controls Page 81-83 refers. Option B. cylinder. Correct Answer is. the fine pitch position. latches are used on shutdown to stop spring pressure pushing the blades to the feather position thus making the load on the engine excessive for the next start. The limits for blade angle are controlled by pitch stops on the. counteract CTM. when stationary. when stationary. 56. counteract ATM. The range of angles of a VP propeller is usually limited by. Option B. Question Number.coarse and fine. Explanation. Explanation. Counterweights are fitted to blade root to. Question Number. 59. The purpose of fine pitch stop is to. Option A. maintain constant speed in flight. Option B. prevent the propeller moving below flight fine pitch in flight. Option C. maintain maximum RPM at takeoff. Correct Answer is. prevent the propeller moving below flight fine pitch in flight. Explanation. CAIP's Leaflet PL/1-1 para 5.2.2 refers. Question Number. 60. Which best describes a Variable Pitch propeller?. Option A. The blade angles can be changed in flight. Option B. Its blade angles are set with an automatic system with which the pilot has no input. Option C. Its blade angles can only be set on the ground. Correct Answer is. The blade angles can be changed in flight. Explanation. propellers which can only be adjusted on the ground are known as 'ground adjustable' not 'variable pitch'. Question Number. 61. The holding coil of a hydromatic propeller feathering button switch holds a relay closed that applies power to the propeller. Option A. dome feathering mechanism. Option B. feathering pump motor. Option C. governor. Correct Answer is. feathering pump motor. Explanation. The feathering pump is required as the existing pressure from the engine will be decaying. The pump is held energised until the prop feather switches sense that the propeller has reached the feather position. Question Number. Option A. Option B. 62. The primary purpose of the front and rear cones for propellers that are installed on splined shafts is to. prevent metal-to-metal contact between the propeller and the splined shaft. reduce stresses between the splines of the propeller and the splines of the shaft. Option C. position the propeller hub on the splined shaft. Correct Answer is. position the propeller hub on the splined shaft. Explanation. AC65-12A. Question Number. 63. The constant-speed control unit is also called a. Option A. propeller pitch control. Option B. accumulator. Option C. governor. Correct Answer is. governor. Explanation. NIL. 17.3. Propeller Pitch Control. Question Number. 1. When the compressive force on a speeder spring is reduced, the propeller blades will. Option A. remain fixed. Option B. fine off. Option C. coarsen. Correct Answer is. coarsen. Explanation. Aircraft Propellers and Controls. Question Number. 2. A hydraulic pitch lock is utilised in a hydromatic propeller to. Option A. lock out the course pitch oil line in the event of underspeeding. Option B. lock out the fine pitch oil line in the event of overspeeding. Option C. prevent the propeller overspeeding in the event of oil supply failure. Correct Answer is. lock out the fine pitch oil line in the event of overspeeding. Explanation. Refer Jepperson Aircraft Propellers and Controls page 136. Question Number. 3. When in the beta range, the propeller pitch is controlled. Option A. directly from the power lever. Option B. indirectly from the power lever. Option C. directly from the pitch change mechanism to the PCU. Correct Answer is. directly from the power lever. Explanation. Refer Jepperson Aircraft Propellers and Controls Page 102. Question Number. 4. The advantage of the beta range is it allows. Option A. high power settings with higher than normal pitch settings when in flight. Option B. low fine pitch settings with high power. Option C. low power settings with higher than normal pitch setting for ground manoeuvres. Correct Answer is. low power settings with higher than normal pitch setting for ground manoeuvres. Explanation. Refer Jepperson Aircraft Propellers and Controls Page 102. Question Number. 5. If the speeder spring pressure of a CSU is increased the blade will. Option A. coarsen off. Option B. fine off. Option C. will not move. Correct Answer is. fine off. Explanation. Jepperson Aircraft Propellers and Control pages 55-58. Question Number. 6. Option A. fine. Option B. feather. Option C. coarse. Correct Answer is. fine. On an underspeed condition the blades are turned to. Explanation. Jepperson Aircraft Propellers and Controls Page 55-58 refers. Question Number. 7. In a hydromatic propeller with counterweights, what is used to make the propeller move to fine pitch?. Option A. A T M. Option B. engine oil. Option C. centrifugal force acting on the counterweight. Correct Answer is. engine oil. Explanation. Refer Jepperson Aircraft Propellers and Controls Pages 55- 58. Question Number. 8. Relaxing tension on the governor spring will result in the blade coarsening and. Option A. RPM decreasing, manifold pressure increasing. Option B. RPM increasing, manifold pressure increasing. Option C. manifold pressure constant, RPM decreasing. Correct Answer is. RPM decreasing, manifold pressure increasing. Explanation. Refer Jepperson Aircraft Propellers and Controls Page 59. Question Number. 9. The ground fine pitch stop is. Option A. never removed. Option B. removed on the ground. Option C. removed during flight. Correct Answer is. removed on the ground. Explanation. Refer Jepperson Aircraft Propellers and Controls Page 32 Low pitch stop is an alternative name on some applications. Question Number. 10. Option A. underspeed. Option B. overspeed. If governor flywheel overcomes the speeder spring, it indicates. In cruise. Correct Answer is. Correct Answer is. reducing drag in engine failure. When the flyweights fly outwards in a PCU. Option C. Question Number. Explanation. tricking the CSU to believing there is a reduction in speed. what will happen?. Engine starting to reduce propeller torque loading on starter motor. Question Number. Option A. Correct Answer is. Explanation. Blade angle is frozen in last known position. Option C. Option B. . this is known as. 14. 12. overspeed. Question Number. Option A. Option A. 13. reducing drag in engine failure. Blade angle coarsen. Option B. Explanation. onspeed. Option B. Fly-weights will move inwards. thus decreasing the blade pitch to speed the propeller back up. Option C. Blade angle finer. Jepperson Aircraft Propellers and Control Pages 135 Refer. increasing drag. Blade angle finer.Option C. believed to be an alternative to Superfine Pitch. Caips Leaflet PL/1-1 refers to ground fine pitch. If force is applied to the speeder spring. 11. Landing and takeoff. Engine starting to reduce propeller torque loading on starter motor. Correct Answer is. Pitch control using torque measuring is for. Question Number. When is superfine pitch used?. reducing drag in binding. Jepperson Powerplant Page 12-4 refers. Explanation. onspeed. flows in the tubes. Correct Answer is. fine reverse then course reverse. fine reverse then course reverse. Increases. . Option B. low power settings with higher than normal pitch setting for ground manoeuvres. Option A. Option B. from course pitch through plane of rotation course. 15. course reverse then fine reverse. Refer Jepperson Aircraft Propellers and Controls Page 55-58. remains constant. Remains unchanged. What happens to the blade angle?. from fine pitch through plane of rotation. In an on speed condition. Question Number. flows out of the tubes Correct Answer is. Jepperson Aircraft Propellers and Controls pages 55-58 Refers. overspeed. If pressure is increased on the speeder spring. Decreases. Correct Answer is. Option C. Option B. Question Number. On a reversing propeller moving to the maximum reversing angle. Option A. Refer Jepperson Aircraft Propellers and Controls Page 55-58. Explanation. fine reverse then course reverse. remains constant. Explanation. Option A. Option C. Option B. from fine pitch through plane of rotation. Correct Answer is. overspeed. Explanation. Option C. Fine reverse must come before coarse reverse. Explanation. Question Number. rpm increases. from fine pitch through plane of rotation. Decreases. 17. the propeller goes.Option A. oil in the tube. Option C. 16. 21. Option B. Explanation. In a prop with counterweights. flight fine only. nitrogen or air on one side of piston. Correct Answer is. Option B. Question Number.Question Number. ATM. Option B. the engine driven pump. Option A. Option C. Option A. coarse. Jepperson Aircraft Propellers and Controls page 81 refers. 19. Explanation. Governor oil pressure. Question Number. Jepperson Aircraft Propellers and Controls Fig 11-32 refers. Correct Answer is. Correct Answer is. oil pressure on two sides of piston. Explanation. Jepperson Aircraft Propellers and Controls Fig 11. oil pressure for the governor is provided by. Correct Answer is. Option C. 20. A 'double' acting propeller has. If a propeller is in fine pitch and then moves to feather it will pass throug. coarse. All governors have a built in pump. Governor oil pressure. a variable volume pump. Question Number. Option A. a pump in the governor. Centrifugal force acting on the counterweight. Option B. what is used to make it move to fine pitch?. reverse. 18. Option C. Explanation. Jepperson Aircraft Propellers and Controls refer. During normal propeller operation.1 refers. oil pressure on two sides of piston. Option A. Option C. . oil pressure on one side of piston. a pump in the governor. U. Explanation. If the spur gear pump in a single acting propeller governor failed. Option C. 22. Jepperson Aircraft Propellers and Controls Pages 55-58 refer. neither of the lines. oil pressure moving a piston. neither of the lines. blades would move to the feather position. Option B. Explanation. Option B. Option C. Option C. oil pressure moving a piston. Oil for an on-speed condition passes through. Question Number.) governor works on the principle of. manual selection through a gearbox. centrifugal twisting moments. Question Number. Correct Answer is. blades would turn to a coarse pitch. an electrical motor moving a gear segment. the. the fine pitch line. Option C. 25. . Explanation. spring pressure acting against centrifugal force. blades would rotate to a fine pitch. Jepperson Aircraft Propellers and Controls Page 85 refer. Correct Answer is. Option A. 24. blades would turn to a coarse pitch.Question Number. Option A. The constant speed unit (C. Jepperson Aircraft Propellers and Controls Page 62 refer. spring pressure acting against centrifugal force. 23. Jepperson A&P Powerplant Page 12-7/8 refers. Option B. the coarse pitch line. Correct Answer is. Option B. Question Number. a venturi or 'u' tube with mercury. Correct Answer is.S. The hydromatic variable pitch propeller is operated on the principle of. Option A. Explanation. Option A. Jepperson Aircraft Propellers and Controls Fig 11-33 refers. convert linear motion to rotary motion. Correct Answer is. to port oil to the coarse pitch oil line to assist in feathering the propelle. Question Number.U. lubricates the entire propeller system. accelerate the unfeathering process.U. convert linear motion to rotary motion. Question Number. Option C. Option A. boosts engine oil system pressure. convert rotary motion to linear motion. the propeller is feathered using the propeller governor pump. or P. 28. Option B. the propeller is feathered using an electrical feathering pump. provide back up to the governor pump. Option A.C. 26. Option C.Question Number. Correct Answer is. Jepperson A&P Powerplant Page 12-30 refers. Option B. Explanation. Explanation. 27. Correct Answer is. Question Number. The purpose of the pitch change cams is to. assist the governor valve to move. Option B. Option C. prevent windmilling. When an engine fails. . Option A. accelerate the unfeathering process. The purpose of an accumulator in a single acting propeller system is to. the propeller is feathered using an electrical feathering pump. Jepperson Aircraft Gas Turbine Powerplants Fig 12-14 refers. Option A. the propeller is feathered using counterweights. boosts engine oil system pressure. Correct Answer is. 29. Option B. Option C.S. The gear type pump in a C. Explanation. Correct Answer is. Explanation. Option B. 32. Jepperson Aircraft Propellers and Controls Page 59 refers. engine lubrication oil tank. aircraft hydraulic System. Option A. 33. Explanation. Jepperson A&P Powerplant Page 12-26 refers. Question Number. Low torque sensing is used to initiate. Correct Answer is. fine pitch selection. by operating the PCU control Lever. Option C. 30. On a free turbine engine it is possible to vary the propeller RPM whilst the engine RPM remains constant. A propeller control Unit hydraulic system is supplied with oil from the.Explanation. Question Number. Explanation. carrying out the manual feather drill. The PCU lever changes the pressure on the governor spring thus changing the pitch of the blades. PCU oil tank. Question Number. Option C. relighting. Option B. by operating the PCU control Lever. Option A. by operating the Power lever. it is not possible to vary the propeller RPM. Option A. carrying out the manual feather drill. pressure control drop switch. Option B. removing the pump circuit breaker or fuse. When auto feathering has taken place the feathering pump is switched off by. Option A. Correct Answer is. Question Number. engine lubrication oil tank. 31. . The pump is switched off by pressing the alternate action pump switch-part of the manual feather drill. Option B. Option C. blade angle is increased by. Correct Answer is. counterweights and a feathering spring. oil pressure. Question Number. Option B. fining off in the event of pitch lock mechanism failure. To reduce drag during power loss. To save the pilot making minor changes when changing altitude. coarsening. Correct Answer is. Option A. In a single acting propeller.Option C. reducing below flight fine pitch. counterweights and a feathering spring. What is the purpose of the auto coarsening system?. The function of a propeller pitch lock is to prevent the propeller from. auto feathering. Option A. fining off in the event of pitch lock mechanism failure. Option C. To prevent overspeeding in the event of the flight fine pitch stop failing. For a description of this system see Jeppesen Aircraft Propellers and Controls page 136. 34. Jepperson Aircraft Propellers and Controls Page 135 refers. CAIP's Leaflet PL/1-1 refer . Option B. Option A. . Option B. To prevent overspeeding in the event of the flight fine pitch stop failing. CTM. Option C. Explanation.note this is not an auto feather system. Explanation. auto feathering. Question Number. Correct Answer is. 36. 35. CAIP's PL leaflets refer to a pitch lock that holds the fine pitch stop in position. Oil pressure turns the prop to fine. Option C. If the oil pressure is released by the CSU the spring and counterweights drive the prop to feather. Question Number. Correct Answer is. Explanation. but also adds that some manufacturers have a pitch lock device that locks the prop in its last position in the event of failure of the pitch lock mechanism. Explanation. CAIP's PL leaflets refer. Question Number. . Correct Answer is. oil pushes the prop to coarse. Explanation. Prevent CTM. Prevent Propeller moving to superfine. 40. Option C. 37. 38. If the oil pressure is released by the CSU the spring and counterweights drive the prop to feather. a separate feathering oil tank. superfine pitch stop. a feathering reserve in the engine oil tank. Oil for the feathering system is taken from. oil pushes the prop to fine. The minimum propeller pitch is established by the. Question Number. Correct Answer is. a feathering reserve in the engine oil tank. In a two position propeller. Option A. Oil pressure turns the prop to fine. the engine lubrication system. ATM turns the prop to fine. Prevent feathering of the prop on shutdown. Option C. Correct Answer is. Option A. Option A. Option B. pitch Lock. CAIP's PL leaflets refer. flight fine pitch stop. Option B. What are the centrifugal latches in a single acting propeller used for?. Option C. Explanation. Option B. Question Number. superfine pitch stop. Question Number. oil pushes the prop to fine. 39. Correct Answer is. Prevent feathering of the prop on shutdown. Option C. Explanation. Jepperson Aircraft Propellers and Controls Page 10 refers. Jepperson Aircraft Propellers and Controls Fig 11-4 refers. Option A. Option B. Explanation. Option B. Option B. less than centrifugal force. Jepperson aircraft propellers and controls Page 96 Refers. Option B. Question Number. the same as centrifugal force. An accumulator may be fitted to. The accumulator is needed to drive the prop out of feather and hence get it rotating. Option A. more than centrifugal force. Correct Answer is.Explanation. less than centrifugal force. feather the propeller. 41. Engine RPM is sensed via the governor bob weights. Correct Answer is. Question Number. Option A. . the CSU is sensing. thus they have more force than the spring. 43. When the engine is running. engine RPM. Question Number. Option A. Option B. An overspeed condition causes governor spring pressure to be. 42. Option C. engine RPM. Option C. Option C. governor weights will pivot inwards raising the governor valve allowing the blades to move to a coarser pitch. Correct Answer is. Option A. propeller tip speed. 44. propeller blade angle. unfeather the propeller. governor weights will spring outwards raising the governor valve allowing the blades to move to a finer pitch. Explanation. unfeather the propeller. The bob weights lift the governor valve in this condition. Question Number. If governor weight spring pressure is reduced. Normally seen on a single acting propeller system. provide emergency control. Explanation. the CSU will. 46. underspeed. Explanation. Question Number. Option C. Correct Answer is. change the blade angle to provide constant RPM. remain constant. Option A. If it is facing into a headwind it will. Question Number. Correct Answer is. Option B. Option B. speed up. increase the blade angle to provide constant RPM. This causes blade to coarsen off to stop overspeeding and as a result the speed remains the same. increase the blade angle to provide constant RPM. overspeed. 45. underspeed. governor weights will spring outwards raising the governor valve allowing the blades to move to a coarser pitch. Explanation. Explanation. Option C. Explanation. remain constant. Option A. decrease the blade angle to provide constant RPM. slow down. Option A. Question Number. The prop will coarsen off and the speed will remain the same. Option B. Option C. Jeppersen Aircraft Propellers and Controls Page 57 refers. overspeed. A constant speed variable pitch propeller is running whilst stationary on the ground. . When governor spring load is less than governor weights. Correct Answer is. governor weights will spring outwards raising the governor valve allowing the blades to move to a coarser pitch. the CSU is in. 47. A headwind acts the same as increased forward speed. When 'on speed' spring pressure equals the governor centrifugal force. If the TAS of an aircraft increases. Correct Answer is.Option C. Stop lugs in the teeth of the rotating cam. 51. Correct Answer is. AC65-12A. Option B. Electric cut-out pressure switch. Electric cut-out pressure switch. AC65-12A. AC65-12A. Option C. Option C. refers to the most fuel efficient pitch range to use at a given engine RPM. Explanation. By varying teh engine RPM except for feathering and reversing. block governor oil pressure to the cylinder of the propeller. Explanation.Question Number. Option C. 49. Correct Answer is. An aircraft's propeller system beta range. is used to produce zero or negative thrust. Option B. is used to produce zero or negative thrust. Correct Answer is. Option B. Correct Answer is. block governor oil pressure from the cylinder of the propeller. Question Number. Option A. is used to achieve maximum thrust during take-off. Option C. 48. port governor oil pressure to the cylinder of the propeller. Beta range is used on the ground. Pulling out the feathering push-button. How is the oil pressure delivery on a hydromatic propeller normally stopped after the blades have reached their full-feathered position?. block governor oil pressure from the cylinder of the propeller. . Explanation. By engine power lever. 50. Question Number. Explanation. Option B. Option A. Option A. How is a propeller controlled in a large aircraft?. Option A. By engine power lever. Question Number. Independently of the engine. Manually feathering a hydromechanical propeller means to. High speed and high pitch angle. Constant speed non-feathering McCauley. Question Number. Option B. 54. Option A. oil pressure. Explanation. AC65-12A. High speed and low pitch angle. 53. Explanation. AC65-12A. increasing the lift coefficient of the blades. adjusting blade angle for most conditions encountered during flight. Option B. unfeather the propeller. AC65-12A. Option B. Correct Answer is. . spring pressure. High speed and low pitch angle. Option A. Option C. Counterweights on constant-speed propellers are generally used to. Option A. A constant speed propeller provides maximum efficiency by. increase blade angle. Hartzell and other propellers of similar design without counterweights increase pitch angle using. Correct Answer is. Option B. increase blade angle. Low speed and high pitch angle. Explanation. 55. Option C. Option C.Question Number. Question Number. What are the rotational speed and blade pitch angle requirements of a constant-speed propeller during take-off?. oil pressure. 52. Option A. Correct Answer is. centrifugal twisting moment. Question Number. decrease blade angle. within 100 rpm of the master. within 100 rpm of the master. Explanation. Correct Answer is. Correct Answer is. Refer Jepperson Aircraft Propellers and Controls Page 134. Option A. Correct Answer is. Option C. . Option B. 17. the same speed as the master. Question Number. 1. Option B. Explanation. match propeller tip speed. AC65-12A. 3. within 20 rpm of the master. pulse probes and a single synchrophase unit. Option C. Synchronising can only be achieved if the slave propeller is. Option A. Jepperson Aircraft Propellers and Control page 132 refers. tachometers and correction motors. pulse probes and a single synchrophase unit. Option B. 2. coordinating the rpm of each engine. match propeller tip speed. match engine rpm. Synchrophasing reduces vibration by the use of. Explanation. Question Number. match blade phase angle difference. Option C. adjusting blade angle for most conditions encountered during flight. Option A.Option C. increasing blade pitch as the aircraft speed increases. Question Number. Synchronising is carried out to.4 Propeller Synchronising. Correct Answer is. in flight except landing and take off. Explanation. 4. reduce vibration and noise. . Explanation. in flight except landing and take off. 6. Correct Answer is. RPM. reduce the pitch of the fastest running blade. Option C. in flight. Synchronisation is used to. Option A. Refer Jepperson Aircraft Propellers and Controls Page131.Explanation. preset the phase angle of propellers. The synchronisation governor monitors. switching on the synchronizer then adjust the engine rpm so that all engines adjust together. 7. Option C. on the ground. Option A. Explanation. Jepperson Aircraft Propellers and Controls Page 37 refers. Question Number. Correct Answer is. reduce vibration and noise. Jepperson Aircraft Propellers and Control Page136 refer to Auto Feather systems. Option B. Question Number. Option C. propeller tip speeds. adjusting the engine rpm then propeller rpm to required speed then switching on. 5. Question Number. Jepperson Aircraft Propellers and Control page 132 refers. Option B. The propeller synchronising system is put into operation by. Question Number. Correct Answer is. Option B. Option A. adjusting the engine rpm at required cruise speed then switching on the synchroniser. Option A. Synchronisation is used. RPM. Option C. Option B. thrust tip speeds. 8. 10. Synchrophasing is lost and the engines continue to function normally. 9. Explanation. rotates (controls) the slave engine governor. the synchrophasing system of a two-propeller aircraft. 11. Option A. Correct Answer is. Option A. Unlike the automatic synchronizing system. PCU governor. Option C. Option B. Explanation. power lever. sets the blade phase angle of two constant speed propellers. Option C. an electric actuator. prop lever. Option B. causes the same rotation speed of the two propellers. Option A. Propellers are synchronised by the. Option B. sets the blade phase angle of two constant speed propellers. Question Number. Correct Answer is. Explanation. PCU governor. In a propeller synchrophasing system. Jepperson aircraft propellers and controls Page 132 Refers. . Option A.Correct Answer is. Synchrophasing is the setting of blade phase angle difference to minimise vibration. Correct Answer is. turns the flexible shaft leading to the trimmer assembly. Explanation. Option C. adjusting the engine rpm at required cruise speed then switching on the synchroniser. Jeppesen Propellers and controls Fig 13-20 shows the actuator attached to the governor. matches the blade angle of variable pitch propellers. rotates (controls) the slave engine governor. Question Number. Question Number. Question Number. EHJ Pallett Aircraft Electrical Systems Page 182 refers. If one signal is lost into the comparator unit when Synchrophasing is operating. equalizes the governor signals. Correct Answer is. Option C. Synchrophasing is used in conjunction with synchronising to reduce aircraft vibration. 13. Synchrophasing is lost and the engines continue to function normally. The governor is sometimes known as a comparator unit. 12. Option B. the slower engine immediately goes to feather. Synchronisation controls RPM within what range?. 150 RPM. at which the slower of the engines is then feathered. Correct Answer is. Question Number.Option B. Explanation. Anytime. of commonly. 14. Option A. both engines remain running until there is a difference. Jeppersen Aircraft Propellers and Controls Page 132 refers. (4 to 5 percent). governor. During cruise. Option A. Option C. When should synchronisation be used?. 50 RPM. Option B. 100 RPM. governor. propeller lever. . During cruise. Explanation. Correct Answer is. RPM Levers. Option C. Option A. Correct Answer is. Question Number. 100 RPM. Explanation. Option B. Jeppersen Aircraft Propellers and Controls Page 132 refers. Propeller Synchronizing works utilizing. Explanation. During landing. Question Number. Option C. 16. Option B. In relation to a propeller aircraft. adjusting the plane of rotation of all propellers. Explanation. A propeller synchrophasing system allows a pilot to reduce noise and vibration by. Option B. Synchrophasing can be used on any multi propeller driven aircraft. all Multi engine aircraft. Explanation. Option B. adjusting the phase angle between the propellers. setting the RPM of all propellers exactly the same. A propeller synchronising system allows a pilot to reduce noise and vibration by. Option C. adjusting the phase angle between the propellers. Correct Answer is. Option C. all Aircraft. NIL. . Option C. Correct Answer is. setting the RPM of all propellers exactly the same. Correct Answer is. 18. turbo prop Aircraft. 65-12A. setting the RPM of all propellers exactly the same. Explanation. To control engine RPM and reduce vibration. Option B. Option A. To control the power output of all engines.Question Number. 15. Option C. Option A. adjusting the plane of rotation of all propellers. Option A. Question Number. Explanation. 17. Option A. adjusting the phase angle between the propellers. Correct Answer is. To control tip speed of all propellers. Question Number. What is the function of automatic propeller synchronizing system on multiengined aircraft?. 65-12A. all Multi engine aircraft. synchrophasing would be used on. Question Number. To control engine RPM and reduce vibration. Jepperson Aircraft Propellers and Control page 124 refers. Electrically de-iced propeller slip rings have regular resistance checks for. using iso-propyl alcohol de-icing fluid sprayed on the blade. open circuit heating elements. Option C. Option A. using iso-propyl alcohol de-icing fluid sprayed on the blade. wear between brushes and slip ring. Option B. . propeller control levers. A pair of slip rings conduct power to the heating elements CAIP's leaflet PL/1-4 refers. Option C. Propeller anti-icing may be achieved by. propeller governors. propeller governors. Option B. On most reciprocating multiengined aircraft. oxidisation due to altitude. a using hot air from the compressor. Option A. open circuit heating elements. Explanation. 19. Correct Answer is. automatic propeller synchronization is accomplished through the actuation of the. Question Number. AC65-12A. Option C.Question Number. Option A. Correct Answer is. throttle levers. Correct Answer is. Question Number.5 Propeller Ice Protection. using commercial de-icing fluid sprayed on the pro. 1. Explanation. Explanation. Option B. 2. 17. Insulation testing of electrical de-icing systems should be periodically carried out because of. CAIPs leaflet PL/1-4 refers. Trailing edge. short/open circuits in the heating system wires along the propeller blade. Option C. Option C. Root. deposits formed due to the wear of slip ring and brush gear assembly. Option B. viewing the blade and observing ice falling off the blade. oxidation of slip ring and brush gear assembly. Refer Jepperson Aircraft Propellers and Controls Pages 126-127. Question Number. Root. Question Number. Explanation. Question Number. 6. viewing the deicing fluid level sight glass. Tip. Option A. Option A. Explanation. CAIP's Leaflet PL/1-4 Para 3. De-icing of the propeller can be monitored by. an ammeter in the flight deck. short/open circuits in the heating system wires along the propeller blade. Explanation. Option C. Option A. Option B. Correct Answer is. Option A. Insulation checks on propeller electrical heating elements should be carried out frequently due to. 5. Where is the de-icing boot?. Jepperson Aircraft Propellers and Control page 129 refers. an open circuit in one of the blades. 3. an open circuit in one of the blades.3-2 Refers. Option C. wear on the slip rings. Correct Answer is. Correct Answer is.Question Number. Correct Answer is. Option B. oxidation due to atmospheric conditions. an ammeter in the flight deck. . Explanation. Option B. 4. Ice is removed from blades by. Option C. Jepperson Aircraft Propellers and Controls Page 126 refers. Option C. inboard and outboard boot sections heated in sequence by action of the timer. inboard and outboard boot sections heated in sequence by action of the timer. Electrical power supplies on large aircraft. Explanation. Explanation. 8. 9. Jepperson Aircraft Propellers and Controls Page 124 refers. Under gravity to the slinger ring then on to the blade. for electrical deicing are. Pump to a slinger ring. Question Number. electrical heating elements bound in rubber overshoes on the blade leading edges. Correct Answer is. Explanation. Option A. Option A. a continuously heated electrical boot. Correct Answer is. Option B.Question Number. Question Number. AC. 10. Option C. How is anti icing fluid fed to the individual blades?. Correct Answer is. Propeller blades are de-iced by. 7. rubber boots inflated in sequence using compressor hot air. Jepperson Aircraft Propellers and Controls Page 126 refers. electrical heating elements bound in rubber overshoes on the blade leading edges. DC. generating eddy currents in the blade. Both AC or DC. Option A. Pump to a slinger ring. Option B. CAIPs PL leaflets Refer. DC. electrical heating elements wound around rubber shoes. Option C. Explanation. Question Number. Correct Answer is. . Pump to each blade rubber feed boot. Option B. Option A. Option B. Jepperson aircraft propellers and controls Page 124 Refers. at high air temperature. Option C. providing constant feed once released. Propeller slip rings. Option A. the hand pump. an electrical pump. Correct Answer is. Question Number. a tank in the prop hub. at high air temperature. 13. an electrical pump. a cyclic timer. Question Number. 12. Option A. The output of an anti-icing pump is controlled by. Correct Answer is. Option B. at low air temperature. 14. Option C. Explanation. Explanation. Option A. Correct Answer is. conduct electrical power for de-icing. Option C. a rheostat. Option B. a rheostat. convey oil for PCU to pitch change mechanism. Option A. Question Number.Question Number. Correct Answer is. On an electrical deicing system fast cycle is used. . conduct electrical power for de-icing. minimise slip. Rolls Royce page 151 refers. Slow cycle meaning the elements are on for longer. Option B. Jepperson Aircraft Propellers and Controls Page 126 refers. 11. on the ground. De-icing fluid goes to a slinger ring from. Option B. Explanation. a hand pump. Option C. feeling the sequence of boot heating and have an assistant observe the loadmeter indications. Option B. increasing cyclic timing. increase cycle times. To increase anti icing effectiveness. 16. Question Number. Option B. Correct Answer is. increase the AC or DC current. Option A. Correct Answer is. Option A. checking the torque meter for abnormal readings. . Disturbed airflow due to ice will reduce the eficiency of the propeller. Question Number. Usually a slow and fast cycle are provided. Option A. visually checking for ice on the blades. increasing cyclic timing. Option C. Option B. Question Number. increasing the AC or DC voltage. increasing propeller RPM. Proper operation of electric deicing boots on individual propeller blades may be best determined by. 17. Correct Answer is. Explanation. Option A. Option C. use liquid as well as electrical anti icing systems. Question Number. increase the AC or DC current. The pump is controlled by a rheostat to quicken or slow the flow. 15. Anticing refers to fluid deicing in Jeppersen Propeller and Controls page 123 therefore it is the rheostat that is adjusted to vary current. Option C. Propeller de-icing for varying rates of icing can be varied by. checking the the de-icing ammeter. 18. Explanation.Explanation. checking the torque meter for abnormal readings. Propeller De-icing can be checked by. Explanation. decrease available engine power. Option C.6 Propeller Maintenance. Correct Answer is. will. Correct Answer is.Option B. Question Number. Option B. 19. Propeller fluid anti-icing systems generally use which of the following?. Option B. 65-12A. 17. Rheostat. Explanation. Explanation. Option A. What unit in the propeller anti-icing system controls the output of the pump?. Explanation. Correct Answer is. feeling the sequence of boot heating and have an assistant observe the loadmeter indications. Option A. Pressure relief valve. Option C. Rheostat. 20. Explanation. Question Number. decrease thrust and cause excessive vibration. feeling the boots to see if they are heating. Ethylene glycol. Isopropyl alcohol. Correct Answer is. Question Number. Cycling timer. Option C. decrease thrust and cause excessive vibration. Ethyl alcohol. 21. when the aircraft is in flight. Option B. Option C. Ice formation on the propellers. Option A. observing the ammeter or loadmeter for current flow. increase aircraft stall speed and increase noise. Isopropyl alcohol. 65-12A. 65-12A. . 65-12A. dynamic balance. Question Number. 30 times to the depth of damage. Correct Answer is. 10 times the depth of damage. Correct Answer is. Option C. it must not be cut back. 2. Option C. it may be cut back. 5 times the depth of damage. 5 times the depth of damage. Explanation. Option B. 3. Option C. 10 times to the depth of damage. thrust balance. Option A. Option A. Correct Answer is. Thrust and camber faces of a propeller should be blended out to. Option A. Question Number. Option B. If the tip of an electrical overshoe is torn. Answer found in unattributed notes. 30 times to the depth of damage. torque balance. Option B. it may be classified as acceptable damage. Leading edges should be blended out to.Question Number. Explanation. Option B. Option A. 10 times the depth of damage. NIL. An aerodynamic correction factor that is preceded by the letter Q indicates. Question Number. 4. Explanation. . Answer found in unattributed notes. Option C. 30 times the depth of damage. torque balance. 1. 8. no repairs. lanolin. 6. it must not be cut back. Option A. Option B. The shank of the propeller is permitted to have. Option B. 0. 0. Option C. repairs using sawdust and aeroglue. no decals fitted. no repairs. Correct Answer is. Option A. the additional metal to be removed for stress relief is.Correct Answer is.002 inch. Option A. repairs using sawdust and aeroglue. 0. 0. Question Number. 7. Option A.02 inch. 5. Refer Jepperson A&P Powerplant Page 12-55. Jepperson A&P Powerplant page 12-53 refers.2 inch. Option C. Correct Answer is. . The preservative used to protect metal blades is. Question Number. Option B. minor repairs. Explanation.002 inch. Question Number. Explanation. Correct Answer is. When blending out a gouge on the face or camber side of a blade. repairs that do not affect weight and balance. Question Number. NIL. Explanation. Explanation. Wooden propellers are permitted. Option C. no repairs. NIL. 925. Must be composite specialist organization. Option A. Question Number. Option B. any approved composite repair facility. Airworthiness Notice 75. any approved composite repair facility. Details of propeller overhaul may be found in. the operator. Correct Answer is. Correct Answer is. lanolin. 9. the AMM. Correct Answer is. petroleum jelly. Option C. 11. Question Number. in the rigging position. Option C. Refer CAA Airworthiness Notice 75. Question Number. Explanation. . Option B. Airworthiness Notice 55. Airworthiness Notice 75. 10. Option A. tail wheel on the ground. Composite propellers may have minor repairs carried out by. Correct Answer is. Explanation. tail wheel in the take off position. The ground clearance of a single engine tail wheel aircraft propeller is measured with the aircraft. Option C. Option B. any approved 3rd party maintenance organization. Explanation. Option C. Option A.Option B. tail wheel in the take off position. Refer JAR 25. brown storage wax. NIL. Explanation. Correct Answer is.925. Explanation. Question Number. Correct Answer is. 18 inches. Cropping is permitted to a maximum of. Feather. 1 inch on all blades. Sometimes known as tip clearance. Option B. The structural clearance of a multi engine aircraft propeller. 18 inches. Option C. Option B. Correct Answer is. 9 inches. . Option A. Question Number. 13. Zero pitch. Correct Answer is. Refer JAR 25. Explanation. 14. Explanation. Explanation. ½ inch on one blade only. Full reverse. 1 inch. Option C. NIL. ½ inch on all blades. Option C.Question Number. is taken between the prop and the fuselage. Option A. is taken from the ground. Feather. Option A. 1 inch on all blades. Option A. The ground (sea) clearance of a sea plane propeller is. is taken between the engines with the props aligned. Question Number. 12. Option C. What position should the blades be when installing the pitch change mechanism onto a hydromatic propeller?. 15. Option B. If 1 blade is cropped all must be cropped equally. is taken between the prop and the fuselage. Jepperson Aircraft Propellers and Controls Fig 2-5 refers. Option B. is due to the power stroke of the engine and may have a more detrimental effect than aerodynamic vibration. Refer Jepperson Powerplant Page 12-12. Aerodynamic Correction Factor (A C F). Jepperson Aircraft Propellers and Control page 16 refers. is indicated in the form of degrees and minutes of pitch. A metal propeller may be statically balanced by. 17. Question Number. Correct Answer is. Refer Jepperson Powerplant Page 12-60. Option B. corrects for dynamic balance. a tracking check. Question Number. Correct Answer is. Correct Answer is. 16.Question Number. Correct Answer is. Explanation. Mechanical vibration relating to propellers in a piston powered aircraft. corrects for static balance. Question Number. removing metal from the opposite blade. Option B. Option B. Option C. Dynamic balance is confirmed by use of. adding or removing lead wool to the hollow blade roots. 19. adding or removing lead wool to the hollow blade roots. adding varnish to the lighter blade. a vibration analyser. . Option C. Option C. is due to the lead lag of the propeller compared to the engine. Option A. is indicated in the form of degrees and minutes of pitch. a vibration analyser. is due to the power stroke of the engine and may have a more detrimental effect than aerodynamic vibration. is due to the crankshaft at intermittent power settings. knife edges and mandrel. Option A. Option C. 18. Explanation. Option A. Option A. Option B. Explanation. 21. Option C. Option B. by maintaining a smooth depression. Explanation. Explanation.rich mixture cools the cylinders. fully aft with the mixture at rich. Question Number. Jepperson Aircraft Propellers and Controls Page 37 refers. Option C. Question Number. 20. at a steeper angle. on the ground with the engine running.Explanation. Correct Answer is. A C F adjusts individual blade pitch angle to compensate for aerodynamic differences of blades in manufacture. Option B. prop at fine to prevent overstressing the engine. Option A. Option B. fully aft with the mixture at idle. Operation with the engine at maximum boost should be limited to. Correct Answer is. prop at course to prevent overstressing the engine. by not exceeding 25% of the chord. Maximum Boost indicates maximum power is applied to the prop. Explanation. 23. Question Number. Option A. on the ground with the engine stationary. Option C. Jepperson Powerplant Page 2-16 refers. When on the ground with the engine idling the prop control should be. 22. Correct Answer is. in flight. Damage to a leading edge can be blended in comparison to a blade face. Option B. prop at windmill to prevent overstressing the engine. Option A. Option C. Question Number. Option A. fully forward with the mixture at idle. on the ground with the engine stationary. prop at course to prevent overstressing the engine. . A propeller with an adjustable blade can be adjusted. fully aft with the mixture at rich. blended within limits. Option A. 1/2 inch. Correct Answer is. . the same frequency as turbine vibration. at a steeper angle. Question Number. Explanation. Option C. any 2 blades. 2 Opposite blades. 24. Option B. left for up to 12 months. any 2 blades.Correct Answer is. 1/2 inch. 2 Adjacent blades. A line of indentations at one blade section can be. Option B. Explanation. Option C. Question Number. Explanation. The longitudinal clearance between the nose wheel and the propeller on a tricycle geared propeller is. A tracking check compares. Question Number. Refer Jepperson Aircraft Propellers and Controls Page 32. 26. Option B. 9 inches. Option C. Option A. Correct Answer is. Correct Answer is.925. 27. 25. Option A. Question Number. declared unserviceable. Option A. 18 inches. Propeller vibration due to a problem with propeller installations would have a. 10:1 compared to 30:1. declared unserviceable. Explanation. Jepperson Aircraft Propellers and Control Page 126 Refer. Refer JAR-25. Option C.Option B. Explanation. Option C. Question Number. Option B. Correct Answer is. Option A. A Prop moved to coarse pitch will rotate the engine without overspeeding. blade distortion. lower frequency than turbine vibration. aerodynamic imbalance on the blades. 30. Preloading propeller blades before installation prevents. Option B. blade flutter. Fine pitch. Negative pitch. Option C. Question Number. Explanation. Correct Answer is. higher frequency than turbine vibration. Preloading refers to shimming the blade gear boss when being mated with the bevel gear cams in the hub. Refer Jepperson Aircraft Propellers and Controls Fig 1-7. blade flutter. 28. Propeller RPM is always less than Gas Turbine RPM therefore vibration frequency will always be less. the blade should be put into what position to stop propeller overspeed?. Option C. Correct Answer is. bevel protractor. Question Number. Option B. 29. Coarse pitch. Coarse pitch. lower frequency than turbine vibration. Option A. propeller protractor. Option A. Explanation. Explanation. propeller protractor. . Blade angle is measured using a. When unfeathering a propeller. clinometer. Correct Answer is. conversion of rough or sharp edges into smooth depression. Option B.Blending is the smoothing of a defect. With a propeller defect. Option C. In the Beta range. 33. Option C. matching of paint finishes for appearances. Fuel temperature. cropping. Option B. 34. lower than a turbine defect.Question Number. Removal of material from the propeller blade tips. Jepperson Aircraft Propellers and Controls Page 21. Option A. Question Number. Correct Answer is. The fuel flow increases. RPM and EGT. Explanation. Option B. angle of attack increases. topping. RPM and EGT. higher than a turbine defect. 31. . Question Number. cropping. If you crop one blade (normally 1 inch maximum) the opposite blade must also be cropped. Explanation. repainting of blade tips after cropping. higher than a auxiliary gearbox defect. tipping. Option C. Correct Answer is. lower than a turbine defect. conversion of rough or sharp edges into smooth depression. Option A. Blending of propeller blade defects refers to the. Option B. the frequency of vibration will be. resulting in a reduction in propeller diameter is called. Option A. Correct Answer is. Option A. Propeller vibration is always lower then turbine vibration. Question Number. 32. Option C. Explanation. and what else increases?. If fuel flow increases then RPM and EGT of the Gas Generator must increase. Explanation. Correct Answer is. EPR and fuel temperature. Explanation. determine the reference blade station. 38.Question Number. Option B. adding lead wool to the blade shank. Option C. Which of the following functions requires the use of a propeller blade station?. Correct Answer is. 37. Propeller balancing. check date stamp for serviceability. etch the propeller serial number to the rear face. Option B. Jepperson Aircraft Propellers and Controls Page 30 refers. Measuring blade angle. ensure the propeller blade is at the horizontal. cut in half with a hacksaw and etch a unique serial number to both halves. Jepperson Aircraft Propellers and Controls Page 3 refers. Jepperson Aircraft Propellers and Controls Page 33 refers. determine the reference blade station. Explanation. cut in half with a hacksaw and etch a unique serial number to both halves. Indexing blades. Correct Answer is. Blade tracking is adjusted by. Measuring blade angle. 36. re-seating the propeller on the front and rear cones. Option A. Question Number. Option C. coat in Engineers blue to ensure seating in the propeller front boss. by fitting shims to the propeller shaft hub. Option B. Option A. Prior to using the universal propeller protractor. Correct Answer is. Option C. 35. . Option C. Question Number. by fitting shims to the propeller shaft hub. Question Number. Explanation. To fit a new front cone to a prop shaft firstly. Option A. Correct Answer is. Option B. Option A. 40. Option B. Option B. Explanation. Option C. reference Torque. balanced. Rolls Royce Jet Engine Page 137. fine pitch setting and advance the engine to the max RPM setting. NIL. fine pitch setting and advance the engine to the target RPM setting. Question Number. Option A. coarse pitch setting and advance the throttle to the target RPM. 42.Explanation. Option C. fine pitch setting and advance the engine to the target RPM setting. reference RPM. Option C. By correcting propeller RPM for ambient Air temperature and barometric pressure. crack checked. Option A. Question Number. Option A. Option B. By comparing compressor and propeller RPM against a reference figure. Question Number. Crack check before re-protection. 39. By comparing torque meter pressure against a reference figure. . 41. Option B. Explanation. To conduct a power check of an internal combustion engine requires. Correct Answer is. Explanation. Immediately after blending out damage to to a blade the repair must be. Correct Answer is. Option C. re-protected against corrosion. Correct Answer is. reference Thrust. crack checked. reference Torque. Option A. How is the efficiency of a turbo prop engine assessed?. Question Number. Jepperson A&P Powerplant Page 2-16 refers. The power output of a turboprop engine is checked by. 1/4 inch maximum difference between adjacent blades. Question Number. 1/8 inch maximum difference between all blades. Option B. Option C. the prop must be tracked. Indentations to the blade face are measured. Option C. Jepperson Aircraft Propellers and Controls Page 43 refers. 46. Explanation. 44. Option A. The limits for a tracking check are. Question Number. Correct Answer is. the heater elements should be checked for continuity and insulation. individually and collectively. no action is required. Explanation. Option A. Taken from unattributed notes. 43. Up to 115% no action is necessary. Option A. Explanation. Correct Answer is. Question Number. . Option B. the heater elements should be checked for continuity and insulation. After a lightning strike. no action is required. return propeller for overhaul. Explanation. By correcting propeller RPM for ambient Air temperature and barometric pressure. 1/8 inch maximum difference between opposite blades. Question Number. Option B. Option B. remove propeller for inspection. Option A.Correct Answer is. Option C. individually. 45. the propeller shaft should be checked for concentricity. 1/8 inch maximum difference between all blades.has anyone got a reference?. Rolls Royce The Jet Engine Page 138 Refers. After overspeeding to 110%. Correct Answer is. Question Number. Correct Answer is. . Ground running an aircraft with a fixed pitch prop with its tail into wind causes the engine RPM to. individually and collectively. The most significant effect of stone chips on a propeller is. structural integrity of the propeller. stay the same regardless of wind direction. increase. Option A. Correct Answer is. Taken from unattributed notes. Explanation. the propeller must be removed and tracked. Option C. 48. Adjustments to a variable pitch propeller are. decrease. Correct Answer is. Explanation. 47. Option C. 50. the propeller must be removed and sent to the manufacturer. CAIPS Lflt PL/1-4 refers inspection after overspeeding depends upon amount of overspeed. Option A. structural integrity of the propeller. 49.has anyone got a reference?. procedure is dependant on the extent of overspeeding. Explanation. Option B. Therefore a tail wind must do the opposite. Option B. Option B. Cracks are initiated by stone chips etc. procedure is dependant on the extent of overspeeding. thrust output of the propeller. Option C. Question Number. collectively.Option C. When a propeller has had a report of overspeeding. Question Number. A head wind on a dead engine will cause the prop to windmill. decrease. Explanation. aerodynamic capability of the propeller. Correct Answer is. Option A. Question Number. When unfeathering a propeller use. made on the ground with the engine running. blades at superfine. A&P Mechanics EA65 states that engines should not be warmed up with a lean mixture and you would not do it with the prop in feather. It is believed that the securing parts stay with the engine. the engine. rich. Option A. rich. any RPM min throttle. Option A. Option B. Option C. Explanation. rich.Option A. Governor spring pressure may be adjusted but only with the engine stationary!!. minimum RPM/min throttle. the engine. Option B. the propeller. Option C. A correspondent reports that for a SAAB 340 the power lever is set at ground idle (940 RPM) and the condition lever at unfeather. Explanation. made in the air using the synchronizer. blades at feather. Question Number. Question Number. Correct Answer is. Correct Answer is. blades at superfine. 51. Option B. the engine load would be too great therefore b must be correct. Option C. made on the ground with the engine stationary. . During engine warm up the mixture should be at. Option B. all separately in cases. the securing parts are kept with. Correct Answer is. 52. Explanation. but no reference can be found to support this. 53. blades at superfine. Option C. Correct Answer is. Question Number. maximum RPM/min throttle. made on the ground with the engine stationary. minimum RPM/min throttle. Option A. lean. Explanation. When a propeller is removed. 54. Question Number. front cones bottomed against the front end of the splines. Explanation. Propeller slip rings should be. Question Number. When measuring RPM on a supercharged engine with variable pitch. Correct Answer is. Correct Answer is. If they do not seat properly the hub cannot be held firm. A splined hub is found be loose with the. maximum boost pressure and actual air pressure is used. Option A. 56. Explanation. CAIPs PL/1-4 para 3. Option A. cleaned and left dry. 57. Explanation. Dial Test Indicator (DTI). cleaned and left dry. Micrometer. lubricated with graphite grease. Option B. How is the concentricity of a propeller shaft checked?. retaining nut torque loading too low. engine boost pressure and actual air pressure is used. Ring gauge. Option A. Option B. Question Number. CAIPs show DTI's checking concentricity of crankshafts etc. See Jeppesen propellers and controls fig 5-19. 55. Dial Test Indicator (DTI). Correct Answer is. Option C. lubricated with silicon grease.2. front cones bottomed against the front end of the splines. Option B. Option B. Cones used to centralise hubs on shafts.8 refers. . Option C. zero boost pressure and actual air pressure is used. excessive spline wear. Option C.Question Number. Option A. Option C. By using a needle file and finish with emery cloth. Lycoming have issued mandatory service bulletin 240S dated 3 Feb 2003 stating that circlips. . 60. 59. annealed and the springiness put back into the circlip before it can be used again.8. 58. Option B.Correct Answer is. How is blending carried out on an aluminium propeller blade?. Correct Answer is. zero boost pressure and actual air pressure is used. used once only. propeller blade angle too large. Option C. CAIPs Leaflet EL/3-2 para 9. static imbalance. The cause of propeller out-of-track vibration is. Option B. Question Number. Option C. used again as long as the circlip springs back first time. blade stiffness not exactly matched. On propeller securing plates circlips should be. Jeppersen Aircraft Propellers and Controls Page 21 refers. Option A. Explanation. Correct Answer is. Option B.3 refers to testing on the fine pitch stops and at the same manifold pressure indicated before the engine was started (IE zero boost). Question Number. Question Number. Option A. Correct Answer is. Vibration caused by blades being out of track means that the blades do not rotate in the same plane of rotation. used once only. By using a scraper. Option C. Variable blade stiffness could cause the blades to flex and thus cause the blades not to track in the same plane. Explanation. By using a needle file and finish with emery cloth. By using a course file and peening. blade stiffness not exactly matched. Option A. lockplates shims and retaining rings must be replaced at overhaul or removal regardless of condition. corrected for. Explanation. Explanation. both systems are working correctly. it remained pressed for about 5 seconds then automatically deselected. the Feathering Pump is Unserviceable since the button did not de-press immediately. These 2 situations would indicate. . there is nothing wrong with the Feathering motor but the Un-Feathering pump is unserv. Question Number. If a 2 blade prop is placed on a knife edge and it ends up horizontal (blades at 3 and 9 o'clock positions). overspeed condition. Option A. Etched on the Propeller. on-speed condition. 62. Explanation. This is a single acting propeller. Painted onto the propeller. On a Hartzell prop with counterweights. 2) When un-feather was selected and the button pressed. Explanation. it remained in for a short period and then autodeselected. Option B. 61. Where would you find information on RPM and Power ratings?. Option A. both systems are working correctly. During a test on the feathering and un-feathering systems. Explanation. The counterweights are the clue here. Option B. full oil supply would indicate. underspeed condition. Option A. 1) after selecting Feather and pressing the feather button. Question Number. overspeed condition. system is a hydromatic type propeller control. 64. Option C. vertically. Correct Answer is. The feather/defeather switch is auto deselected by a pressure switch sensing the pressure build up in the hub after the desired position has been reached. Correct Answer is. Question Number. Option C. therefore if the tank is full the spring must be fully extended to counteract an overspeed condition. it is said to be in balance. Option B. Engine Log book.Question Number. Correct Answer is. Option C. CAIPs leaflet EL/3-2 states that the reference RPM is recorded in the engine log book for power assurance checks. Engine Log book. Option A. 63. blocked scavenge filter. torsional stress. assuming the pump is a full flow (gear) type. Correct Answer is. cracks. Restriction of flow in the circuit. Dye penetrant techniques are used to detect surface cracks. Which of the following defects is cause for rejection of wooden propellers?. No protective coating on propeller. Question Number. Correct Answer is. Question Number. Explanation. cracks. restricted pump operation. Option B. corrosion at the blade tip. 65. Option C. Option C. An oversize hub or bolthole or elongated bolt holes. Explanation. Explanation. Option A. Option A. . Inspection of a propeller blade by dye penetrant inspection is accomplished to detect. Correct Answer is. Question Number. will give this indication. Explanation. Which of the following is used to correct horizontal imbalance of a wooden propeller?. High Engine Oil pressure may be caused by. higher oil pressure. 67. Solder missing from screw heads securing metal tipping. Option C. 68. Solder or finish can be replaced elongated holes cannot. blocked scavenge filter. horizontally. Question Number. Jeppersen Aircraft Propellers and Controls Page 20 refers. Option B. Option C. Correct Answer is. 66.Option B. dynamically. An oversize hub or bolthole or elongated bolt holes. Option B. horizontally. Option A. Brass screws are added for vertical imbalance on the lightwieght side of the hub. Correct Answer is. Harmonic. Explanation.Option A. Option C. AC65-12A. Vertical. What type of imbalance will cause a two-bladed propeller to have a persistent tendency to come to rest in a horizontal position (with the blades parallel to the ground) while being checked on a propeller balance beam?. Option B. Explanation. Vertical. Brass screws. Question Number. Solder. Horizontal. To mark the propeller blades where weights are to be be attached. Question Number. To level the balance stand. Option C. Propeller manufacturers. Shellac. Explanation. Propeller manufacturers. Explanation. 70. 69. Option B. Option C. To support the propeller on the balance knives. Option A. Correct Answer is. CAIPs state that adding solder to the metal tiping of the blade is the correct method for horizontal balance. Option B. Correct Answer is. Airframe manufacturers. Option A. To support the propeller on the balance knives. What is the purpose of an arbor used in balancing a propeller?. . 71. Option A. Engine Manufacturers. AC65-12A. Correct Answer is. Question Number. Option B. AC65-12A. Solder. Which of the following determines oil and grease specifications for lubrication of propellers?. Option C. keeping the propeller blades within the same plane of rotation. fresh water. Correct Answer is. greater at high RPM. The effect of an unbalanced propeller will usually be. 75. NIL. Option A. greater at low RPM. Option A. Option C. may be necessary to achieve final balancing. Option A. 72. correct blade contouring and angle setting. has little or no effect on operating characteristics. correct blade contouring and angle setting. Question Number. Apparent engine roughness is often a result of propeller unbalance. static balancing. AC65-12A. Option C. Option A. may be necessary to achieve final balancing. 74. Option C. Correct Answer is. should never be done.Question Number. Explanation. Question Number. Option B. The application of more protective coating on one blade than another when refinishing a wood propeller. Option B. . approximately the same at all speeds. Propeller aerodynamic (thrust) imbalance can be largely eliminated by. soapy water. 73. greater at high RPM. AC65-12A. Propellers exposed to salt spray should be flushed with. Correct Answer is. Question Number. Option B. Option B. Explanation. Explanation. Option A. By magnetic particle inspection. AC43. By etching. By anodizing. at take-off pitch (maximum thrust) angle. No protective coating on propeller. Explanation. Explanation. Option B. Explanation.Option C. feathered or in the most critical pitch configuration. stoddard solvent. An oversize hub or bolt hole. Option B. Option A. Correct Answer is. 78. By magnetic particle inspection. or elongated bolt holes. or elongated bolt holes. Correct Answer is. Option B. This clearance is with the propeller blades. Which of the following defects is cause of rejection of a wood propeller?. Correct Answer is. Longitudinal (fore and aft) clearance of constant speed propeller blades or cuffs must be at least 1/2 inch (12. JAR 23. feathered or in the most critical pitch configuration. Question Number.13-1B. 77. Option C. . Option A. fresh water. How can a steel propeller hub be tested for cracks?. 76.7 mm) between propeller parts and stationary parts of the aircraft. at the lowest pitch angle. Question Number. An oversize hub or bolt hole. Solder missing from screw heads securing metal tipping. AC65-12A. AC65-12A. Explanation. Option C. Question Number. Correct Answer is. Option C. and grease the blade through the remaining nipple. Correct Answer is. the service manual may recommend on some models to. and grease the blade through the remaining nipple. 81. remove any entrapped air. When lubricating a Hartzell propeller blade with grease. remove one of the two grease nipples for the blade. 82. Rear cone should be moved forward. Option C. Option B. remove any entrapped air. Question Number.Question Number. Rear cone should be moved forward. Blade angles are incorrect. seat the blades fully against the low pitch stop. Explanation. remove one of the two grease nipples for the blade. Question Number. Question Number. remove the seals prior to greasing and reinstall them afterwards. Option C. Correct Answer is. Correct Answer is. 80. Option C. Inspect the bolts for tightness after the first flight and again after the first 25 hours of flying. Option A. Option A. . final track should be accomplished prior to installing the hub in the propeller. NIL. pump grease into both grease nipples for the blade simultaneously. it is necessary to exercise the propeller by moving the governor control through its entire travel several times to. Explanation. Explanation. NIL. Option B. Option C. Option B. Propeller-dome combination is incorrect. NAS close-tolerance bolts should be used to install the propeller. Option A. test the maximum RPM setting of the governor. What is indicated when the front cone bottoms while installing a propeller?. 79. Option A. When running-up an engine and testing a newly installed hydromatic propeller. AC65-12A. Which of the following statements concerning the installation of a new fixed-pitch wood propeller is true?. If a separate metal hub is used. Option B. to prevent damage to the blade seals. the front cone was not fully bottomed against the crankshaft splines during installation. spider-shaft oil seal. Question Number. Option C. Explanation. Option B. NIL. piston gasket. . Oil leakage around the rear cone of a hydromatic propeller usually indicates a defective. Option B. Question Number.Correct Answer is. High RPM. High RPM. High pitch range. 85. Correct Answer is. Option A. Explanation. Question Number. Low RPM. causing the cone seats to act as the high pitch stop. Explanation. the propeller retaining nut was not tight enough during previous operation. AC43. Correct Answer is. Question Number. all ignition and magneto checking is done with the propeller in which position?. Option C. Correct Answer is. spider-shaft oil seal. On aircraft equiped with hydraulically operated constant speed propellers. If the propeller cone or hub cone seats show evidence of galling and wear. 83. Option A. Option A. 86. Option C. AC65-12A. AC65-12A. the propeller retaining nut was not tight enough during previous operation. Option B.13-1B. the pitch change stops were located incorrectly. 84. the most likely cause is. dome-barrel oil seal. Maximum taper contact between crankshaft and propeller hub is determined by using. Explanation. Inspect the bolts for tightness after the first flight and again after the first 25 hours of flying. Option B. Option C. Question Number. Option A. Explanation. Option A. Full decrease.Option A. the positions of the tips of the propeller blades relative to each other. the positions of the tips of the propeller blades relative to each other. a micrometer. Option B. AC65-12A. If a flanged propeller shaft has dowel pins. Question Number. check carefully for front cone bottoming against the pins. install the propeller so that the blades are positioned for hand propping. Full increase. Correct Answer is. . Option C. the propeller can be installed in only one position. low propeller blade pitch angle. Full increase. Propeller blade tracking is the process of determining. 88. the plane of rotation of the propeller with respect to the aircraft longitudinal axis. 89. a surface gauge. Full increase. Explanation. 87. low propeller blade pitch angle. In what position is the constant-speed propeller control placed to check the magnetos?. that the blade angles are within specified tolerance of each other. bearing blue colour transfer. Correct Answer is. Option B. high propeller blade pitch angle. Explanation. AC65-12A. Option A. the propeller can be installed in only one position. NIL. bearing blue colour transfer. Option C. Correct Answer is. Correct Answer is. Explanation. Option B. low propeller blade pitch angle. AC65-12A. Question Number. Option C. Question Number. Option A. 92. sanding and applying a proper filler.13-1B. It is important that nicks in aluminium alloy propeller blades be repaired as soon as possible in order to. . Option C. Option B. Explanation. AC43. Cold straightening only. 93. depending on the location and severity of damage. maintain equal aerodynamic characteristics between blades. 91. Option B. Correct Answer is. eliminate stress concentration points. Option A. eliminate stress concentration points. Option A. filing with a riffle file. Question Number. Correct Answer is. back. equalize the centrifugal loads between the blades. Question Number. Option C. Option C. 90. face. AC43. Option B. Explanation. filing with a half round or flat file. followed by heat treatment to store original strength. shank. but not on the leading or trailing edges of aluminium blades. Repairs of aluminium alloy adjustable pitch propellers are not permitted to be made on the. Option C. Careful heating to accomplish straightening. Correct Answer is.13-1B. Option A. Explanation. may be repaired by first. Question Number.13-1B. AC43. Cold straightening only. Which of the following methods is used to straighten a bent aluminium propeller blade that is within repairable limits?. shank. Option B. Either hot or cold straightening. Minor surface damage located in a repairable area. sanding and applying a proper filler. When preparing a propeller blade for inspection it should be cleaned with. Option B. AC43. Explanation. Dye penetrant inspection. may be repaired by. filing with a riffle file. Correct Answer is. Question Number. . methyl ethyl ketone. NIL. mild soap and water. sanding and applying a proper filler. Option C. Explanation. Option C. filing with a riffle file. Question Number. Question Number. Option C. powdered soapstone. Option A. the affected surface should be polished with. 96. 95. 94. steel wool. Option B. After removal of aluminium blade damage. mild soap and water. Explanation. Minor surface damage located in a repairable area. Correct Answer is. Explanation. very fine sandpaper.Correct Answer is.13-1B. but not on the leading or trailing edges of composite blades. What method would you use to inspect an aluminium propeller blade when a crack is suspected?. AC65-12A. Option A. filing with a half round or flat file. Option A. 97. Option A. Question Number. Option B. very fine sandpaper. fine steel wool. Correct Answer is. NIL. AC43. Any repairs that would require shortening and re-contouring of blades. A transverse crack of any size. Magnetic particle inspection. a major modification. Correct Answer is. . Explanation. Option C. 1/8 inch. Correct Answer is. Option B. NIL. Which of the following generally renders an aluminium alloy propeller unrepairable?.13-1B. Option C. Correct Answer is. Any slag inclusions or cold shuts.Option B. Dye penetrant inspection. Question Number. Option A. A transverse crack of any size. Question Number. Correct Answer is. 98. 99. Question Number. Explanation. a major repair. Option B. What is the acceptable amount of cushion in a governor control lever?. 100. Option C. AC43. Option A. a major repair. A bright light and magnifying glass. Option A. 3/8 inch. 1/4 inch. 1/8 inch.13-1B. Option C. NIL. permitted under the privileges and limitations of a category B1 licence. Explanation. Option B. Explanation. Removal of propeller blade tips within the Type Certificate Data Sheet limits to correct a defect is. 7 Propeller Storage and Preservation. Option B. When storing wooden propellers. aircraft Maintenance Manual. Correct Answer is. Option B. the dark. Explanation. Option C. Question Number. natural light. Question Number. 2. Airworthiness Notices. Explanation. Jepperson A&P Powerplant Page 12-54 refers. Rubber components should be stored in. Option A. Question Number. Explanation. 4. store in a horizontal position. Option A. Correct Answer is. Option B. store in a horizontal position. NIL. Question Number. Option A. aircraft Maintenance Manual. 3. Correct Answer is. A wooden propeller should be stored. Option C. propeller overhaul and repair manual. a dry and well ventilated area. NIL. 1. wrap in greaseproof paper. The maximum storage periods for installed propellers are detailed in the. the dark. flouresent light. . Option A.17. store in a dry well ventilated and illuminated location. Option C. should not be wrapped at-all. Option C. Explanation. 6. Question Number. Correct Answer is. Correct Answer is. should be completely emptied and dried. Explanation. Option A. for storage for long periods should. A&P Technician Powerplant textbook 12-54. a dry and well ventilated area. should not be wrapped at-all. Option B. Question Number. a warm but light storeroom. Option C. Option C. Correct Answer is.Option B. Option B. in a room with high humidity to stop it drying and cracking. NIL. Explanation. be filled with special inhibiting oil to prevent condensation and corrosion. should be wrapped tightly. . A wooden propeller in storage. 5. Option A. be filled with the normal operating oil to prevent condensation and corrosion. should be wrapped loosely. A&P Technician Powerplant textbook 12-54. A VP propeller mechanism. should be completely emptied and dried.