Systems test alpha

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Study guide for the 1st Systems Test

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Systems test alpha

  1. 1. Study Guide (General Description, Flight Controls and Hydraulics, Rotors, and Power Plant)
  2. 2. 1. Define the term WARNING <ul><li>An operating procedure, practice, etc., which if not strictly observed could result in damage to or destruction of equipment. </li></ul><ul><li>A mandatory procedure </li></ul><ul><li>An operating procedure, practice, etc., which if not correctly followed could result in personal injury or loss of life. </li></ul><ul><li>Indicated futurity </li></ul>
  3. 3. 2. Define the term CAUTION <ul><li>An operating procedure, condition, etc., which is essential to highlight. </li></ul><ul><li>An operating procedure, practice, etc., which if not strictly observed could result in damage to or destruction of equipment. </li></ul><ul><li>An operating procedure, practice, etc., which if not correctly followed could result in personal injury or loss of life. </li></ul><ul><li>Indicates futurity </li></ul>
  4. 4. 3. Define NOTE <ul><li>A mandatory procedure </li></ul><ul><li>Recommended or preferred, not mandatory. </li></ul><ul><li>Indicates futurity </li></ul><ul><li>An operating procedure, condition, etc., which is essential to highlight. </li></ul>
  5. 5. 4. Define the term SHALL <ul><li>Indicated futurity </li></ul><ul><li>A mandatory procedure </li></ul><ul><li>An optional procedure </li></ul><ul><li>Recommended or preferred, not mandatory </li></ul>
  6. 6. 5. Define the term SHOULD <ul><li>Recommended or preferred, not mandatory </li></ul><ul><li>An optional procedure </li></ul><ul><li>A mandatory procedure </li></ul><ul><li>An operating procedure, condition, etc., which is essential to highlight </li></ul>
  7. 7. 6. Define the terms MAY or NEED NOT <ul><li>Indicated futurity </li></ul><ul><li>A mandatory procedure </li></ul><ul><li>A condition that you may do or not </li></ul><ul><li>An optional procedure </li></ul>
  8. 8. 7. Define the term WILL <ul><li>An optional procedure </li></ul><ul><li>Indicates futurity </li></ul><ul><li>A mandatory procedure </li></ul><ul><li>A procedure that will be done </li></ul>
  9. 9. 8. The three sections of the TH-67 fuselage are the _____, _______, and the _______ section. <ul><li>cockpit, cabin, and aft boom </li></ul><ul><li>front, intermediate, and back tail </li></ul><ul><li>forward, intermediate, and tail boom </li></ul><ul><li>cockpit, cabin, and tail </li></ul>
  10. 10. 9. The VFR & A+ configuration have one pitot that provides _______ air to the airspeed indicator and two vents that provide _____ air to the static instruments. <ul><li>direct, indirect </li></ul><ul><li>pressure, kinetic </li></ul><ul><li>impact (ram), static </li></ul><ul><li>direct, static </li></ul>
  11. 11. 10. The IFR configuration has __ ______ pitot/static systems. <ul><li>4 separate </li></ul><ul><li>3 individual </li></ul><ul><li>2 independent </li></ul><ul><li>2 individual </li></ul>
  12. 12. 11. The TH-67 ____ light, located on the aircraft nose provides a 450 watt lamp in an extendable and slewable mount. <ul><li>landing </li></ul><ul><li>position </li></ul><ul><li>collision </li></ul><ul><li>search </li></ul>
  13. 13. 12. The TH-67 ____ light, located on the aircraft nose provides a 250 watt lamp in a fixed mount. <ul><li>landing </li></ul><ul><li>search </li></ul><ul><li>position </li></ul><ul><li>collision </li></ul>
  14. 14. 13. How many switches are used to control the search light in the NVG mode on the A+ configuration? <ul><li>2, one for selecting IR light, and one to turn it on. </li></ul><ul><li>4, one to turn it on, one to select white light, one to select IR light, and one to slew the search light to extended and retracted position. </li></ul><ul><li>3, one to select the IR light, one to turn the light on, and one to slew the search light to the desired position. </li></ul><ul><li>2, one on/off switch, and one to select IR. </li></ul>
  15. 15. 14. What does the term semi-monocoque mean? <ul><li>The skin of the aircraft provides all of the structural strength </li></ul><ul><li>The aircraft skin provides none of the structural strength </li></ul><ul><li>The aircraft skin provides some of the structural strength </li></ul><ul><li>None of the above </li></ul>
  16. 16. 15. The TH-67 intermediate section uses a ____ type of construction. <ul><li>semi-rigid </li></ul><ul><li>semi-flex </li></ul><ul><li>semi-monocoque </li></ul><ul><li>monocoque </li></ul>
  17. 17. 16. Which section of the aircraft contains the engine? <ul><li>A. The forward section </li></ul><ul><li>B. The cabin section </li></ul><ul><li>C. The engine/transmission section </li></ul><ul><li>D. The intermediate section </li></ul>
  18. 18. 17. The TH-67 tail boom section uses ___ ______ type of construction. <ul><li>semi monocoque </li></ul><ul><li>partial monocoque </li></ul><ul><li>fully monocoque </li></ul><ul><li>semi rigid </li></ul>
  19. 19. 18. State the purpose of the vertical fin. <ul><li>Provides vertical stability on the x-axis </li></ul><ul><li>The vertical fin, being displaced (canted) 5 ½ degrees to the right thus reducing the tail rotor thrust requirements in forward flight </li></ul><ul><li>Off-loads the tail rotor between 80 and 100 knots </li></ul><ul><li>Provides vertical stability on the yaw axis </li></ul>
  20. 20. State the purpose of the horizontal stabilizer. <ul><li>A. Maintains a desirable aircraft attitude through the high end of the airspeed range. The metal strip at its leading edge provides for autorotational stability. </li></ul><ul><li>B. Provides pitch (up and down) about the lateral axis </li></ul><ul><li>C. Provides horizontal control of the aircraft during low “G” maneuvers. </li></ul><ul><li>D. None of the above </li></ul>
  21. 21. 19. At what airspeed is the tail rotor fully off-loaded in forward flight? <ul><li>Between 110 and 130 knots </li></ul><ul><li>Between 90 and 120 knots </li></ul><ul><li>At 100 knots </li></ul><ul><li>Between 100 and 110 knots </li></ul>
  22. 22. 20. The nomenclature of the TH-67 power plant is the model _______. <ul><li>T700-GE-401C </li></ul><ul><li>JP-WD40 </li></ul><ul><li>PW-123-J </li></ul><ul><li>250-C20J </li></ul>
  23. 23. 21. State the maximum torque available (MAX TQ AVAIL). <ul><li>107% TQ for 15 seconds max </li></ul><ul><li>100% TQ for 5 minutes max </li></ul><ul><li>>85% to 100% for 5 minutes max </li></ul><ul><li>100% TQ for 5 seconds max </li></ul>
  24. 24. 22. State the maximum continuous power (TQ AVAIL CONT) of the TH-67 power plant. <ul><li>85% TQ (270 SHP) no time limit </li></ul><ul><li>85% TQ (270 SHP) take-off power range 5 minute limit </li></ul><ul><li>>85% to 100% TQ maximum </li></ul><ul><li>100% TQ no time limit </li></ul>
  25. 25. 23. Can the maximum transient power setting (110% TQ) be used intentionally? <ul><li>Yes, 5 minutes limit </li></ul><ul><li>Yes, 5 seconds limit </li></ul><ul><li>No, only when executing high ‘G’ maneuvers </li></ul><ul><li>No, intentional use is prohibited </li></ul>
  26. 26. 24. State the diameter of the TH-67 main rotor. <ul><li>52’ 4” </li></ul><ul><li>42’ 4” </li></ul><ul><li>33’ 4” </li></ul><ul><li>44’ 3” </li></ul>
  27. 27. 25. What type of airfoil is the main rotor blade? <ul><li>A honey comb airfoil </li></ul><ul><li>A symmetrical airfoil </li></ul><ul><li>An asymmetrical airfoil </li></ul><ul><li>None of the above </li></ul>
  28. 28. 26. How many degrees of twist are there in the main rotor blade? <ul><li>A positive 10 degrees </li></ul><ul><li>A negative 5 degrees </li></ul><ul><li>A positive 5 degrees </li></ul><ul><li>A negative 10 degrees </li></ul>
  29. 29. 27. State the tail rotor diameter. <ul><li>5’ 10” </li></ul><ul><li>4’ 5” </li></ul><ul><li>5’ 5” </li></ul><ul><li>8’ 5” </li></ul>
  30. 30. 28. How many degrees of pitch are in the tail rotor with full left pedals applied? <ul><li>25 degrees </li></ul><ul><li>23 degrees </li></ul><ul><li>17 degrees </li></ul><ul><li>21 degrees </li></ul>
  31. 31. 29. State the TH-67 Vne <ul><li>122 knots </li></ul><ul><li>78 knots </li></ul><ul><li>130 knots </li></ul><ul><li>100 knots </li></ul>
  32. 32. 29. State the maximum airspeed limitation with >85 to 100% TQ applied. <ul><li>78 knots </li></ul><ul><li>110 knots </li></ul><ul><li>80 knots </li></ul><ul><li>122 knots </li></ul>
  33. 33. 31. State the minimum rate of descent airspeed in autorotation. <ul><li>A. 50 knots @ 394 RPM (100% rotor RPM) </li></ul><ul><li>B. 69 knots @ 394 RPM (100% rotor RPM) </li></ul><ul><li>C. 52 knots @ 394 RPM (100% rotor RPM) </li></ul><ul><li>D. 60 knots @ 394 RPM (100% rotor RPM) </li></ul>
  34. 34. 32. State the maximum glide distance airspeed in autorotation. <ul><li>69 knots @ 394 RPM (100% rotor RPM) </li></ul><ul><li>79 knots @ 394 RPM (100% rotor RPM) </li></ul><ul><li>52 knots @ 394 RPM (100% rotor RPM) </li></ul><ul><li>60 knots @ 394 RPM (100% rotor RPM) </li></ul>
  35. 35. 33. State the minimum crew restriction VFR and IFR. <ul><li>VFR minimum 1 pilot, IFR minimum 1 pilot and 1 observer </li></ul><ul><li>VFR minimum 2 pilots, IFR minimum 1 pilot </li></ul><ul><li>VFR minimum 1 pilot, IFR minimum 2 pilots </li></ul><ul><li>VFR minimum 1 student, IFR minimum 1 student and 1 pilot </li></ul>
  36. 36. 34. State the fuel capacity of the TH-67 fuel cell. <ul><li>69.4 U.S. gallons total; 64.2 U.S. gallons useable; 2.3 U.S. gallons unusable </li></ul><ul><li>81.4 U.S. gallons total; 64.2 U.S. gallons useable; 1.5 U.S. gallons unusable </li></ul><ul><li>69.4 U.S. gallons total; 68.2 U.S. gallons useable; 1.3 U.S. gallons unusable </li></ul><ul><li>84.1 U.S. gallons total; 82.6 U.S. gallons useable; 1.5 U.S. gallons unusable </li></ul>
  37. 37. 35. Why must the engine oil system be drained and refilled if transmission and engine oils are intermixed? <ul><li>To prevent chemical reaction </li></ul><ul><li>To prevent damage to the engine oil seals </li></ul><ul><li>If the two are mixed they become very flammable </li></ul><ul><li>To prevent damage to the transmission </li></ul>
  38. 38. 36. In a conventional helicopter, what are the three basic flight controls that are used to maneuver the aircraft? <ul><li>Throttle, stick, rudder </li></ul><ul><li>Cyclic, stick, collective </li></ul><ul><li>Cyclic, collective, tail rotor (anti-torque) pedals </li></ul><ul><li>Stick, elevator, vertical fin </li></ul>
  39. 39. 37. In a conventional helicopter, which flight control directs the total lift/thrust of the main rotor system? <ul><li>The collective </li></ul><ul><li>The stick </li></ul><ul><li>The pedals </li></ul><ul><li>The cyclic </li></ul>
  40. 40. 38. Which conventional helicopter flight control will input a pitch change to all main rotor blades simultaneously regardless of the blades position? <ul><li>Cyclic </li></ul><ul><li>Rudder </li></ul><ul><li>Collective </li></ul><ul><li>Stick </li></ul>
  41. 41. 39. In a conventional helicopter, the rotation of the main rotor induces a force known as torque. Describe the effects this force has on the fuselage. <ul><li>The torque force will cause the fuselage of the aircraft to rotate in the same direction of the main rotor </li></ul><ul><li>The torque force will cause the fuselage of the aircraft to rotate in the opposite direction of the main rotor </li></ul><ul><li>No effect is observed since rotor torque and fuselage torque will be equalized </li></ul><ul><li>None of the above </li></ul>
  42. 42. 40. State the primary purpose of the tail rotor system in a conventional helicopter. <ul><li>Provides directional control </li></ul><ul><li>Yaws the aircraft </li></ul><ul><li>To counter-act the torque effects of the main rotor </li></ul><ul><li>Provides right and left inputs on a hover </li></ul>
  43. 43. 41. The ___ ____ controls will provide directional control (heading) of the aircraft during hovering, as well as trimming the fuselage of the helicopter at higher speeds. <ul><li>Cyclic pedals </li></ul><ul><li>Stick pedals </li></ul><ul><li>Tail rotor </li></ul><ul><li>A and B </li></ul>
  44. 44. 42. Cyclic control inputs (fore/aft and lateral) are considered independent up to the _____ ______ from there on up to the non-rotating swash plate they are considered ______. <ul><li>intermixing bellcrank, coordinated </li></ul><ul><li>self adjusting controls, manual </li></ul><ul><li>intermixing push rods, coordinated </li></ul><ul><li>self input controls, manual </li></ul>
  45. 45. 43. In the VFR configuration, what happens to the pilot’s cyclic stick if left unattended when the copilot’s cyclic stick is removed? <ul><li>Nothing, there is no difference with both or just one cyclic stick installed/removed </li></ul><ul><li>The reduced load on the balance spring will cause the pilot’s cyclic stick to creep aft slightly </li></ul><ul><li>If this situation is encountered you must not go flying do to lack of controls on the aircraft </li></ul><ul><li>You must maintain right cyclic input to counteract for the missing copilot’s cyclic stick </li></ul>
  46. 46. 44. Where is the cyclic friction knob located? <ul><li>Right on the base of the copilot’s cyclic stick </li></ul><ul><li>There is not such thing installed in the TH-67 helicopter </li></ul><ul><li>In between the pilot and copilot seat </li></ul><ul><li>Left of the base on the pilot’s cyclic stick </li></ul>
  47. 47. 45. How much preload is on the cyclic system with the aircraft running and the hydraulics on? <ul><li>2 to 3 pounds preload </li></ul><ul><li>1 to 1 ½ pounds preload </li></ul><ul><li>2 ½ to 4 pounds preload </li></ul><ul><li>½ to 1 pound preload </li></ul>
  48. 48. 46. Which aircraft configuration has the force trim system? <ul><li>VFR only </li></ul><ul><li>IFR only </li></ul><ul><li>A+ only </li></ul><ul><li>All of the above </li></ul>
  49. 49. 47. What switches are located on the pilot’s collective stick control head? <ul><li>On/off switch, landing light, fuel start </li></ul><ul><li>Search light switches, landing light, governor RPM increase/decrease, and the starter button </li></ul><ul><li>There is no switches on the pilot’s collective stick; all switches are located on the copilot’s collective stick </li></ul><ul><li>Fuel valve switch, landing light, starter button, and hover button </li></ul>
  50. 50. 48. Where is the collective friction located? <ul><li>It is located on the right of the copilot’s collective stick base </li></ul><ul><li>Right behind the pilot’s anti-torque pedals </li></ul><ul><li>It is located on the left of the pilot’s collective stick base </li></ul><ul><li>No such thing installed in the TH-67 helicopter </li></ul>
  51. 51. 49. What switches are located on the co-pilot’s collective control head? <ul><li>The search light switch, landing light, governor RPM increase/decrease, and the starter button </li></ul><ul><li>Fuel valve switch, throttle switch, landing light, and hover switch </li></ul><ul><li>There is no c0-pilot collective control head </li></ul><ul><li>Eject switch, landing light, fuel valve switch, and avionics </li></ul>
  52. 52. 50. What amount of collective control preload is built into the collective flight control system? <ul><li>2 to 4 pound preload </li></ul><ul><li>1 to 3 pound preload </li></ul><ul><li>4 to 6 pound preload </li></ul><ul><li>3 to 5 pound preload </li></ul>
  53. 53. 51. Which collective control stick is removable and why? <ul><li>The co-pilot‘s collective stick is removable in case a non-rated passenger is flown in the co-pilot’s seat </li></ul><ul><li>The pilot’s collective for egress purposes </li></ul><ul><li>Neither the pilot or co-pilot’s collective stick can be removed unless is for maintenance reasons only </li></ul><ul><li>None of the above </li></ul>
  54. 54. 52. Which direction can the tail rotor pedals be adjusted? <ul><li>Forward only </li></ul><ul><li>Aft only </li></ul><ul><li>Pedals are fixed and can not be re-adjusted </li></ul><ul><li>The pedals can be adjusted fore and aft </li></ul>
  55. 55. 53. What changes the pitch (angle-of-attack) in the tail rotor through the lever assembly? <ul><li>The pitch horn </li></ul><ul><li>The tail rotor bell cranks </li></ul><ul><li>The pitch change links </li></ul><ul><li>The anti-torque pedals </li></ul>
  56. 56. 54. What is the preload on the tail rotor system? <ul><li>1 to 3 pounds preload </li></ul><ul><li>3 to 5 pounds preload </li></ul><ul><li>2 to 5 pounds preload </li></ul><ul><li>4 to 5 pounds preload </li></ul>
  57. 57. 55. Does the tail rotor system have hydraulic assist? <ul><li>The tail rotor system does not have hydraulics </li></ul><ul><li>Yes </li></ul><ul><li>Yes, but only in the retreating blade to prevent tail vibrations </li></ul><ul><li>None of the above </li></ul>
  58. 58. 56. The TH-67 flight control system can best be described as ____ ____ ____ with hydraulic assist. <ul><li>fully articulated links </li></ul><ul><li>hydro mechanical linkages </li></ul><ul><li>direct mechanical linkages </li></ul><ul><li>articulated mechanical links </li></ul>
  59. 59. 57. The purpose of the hydraulic servo actuator installed to the cyclic and collective controls is to convert ____ ____ under pressure into ____ ____ work. <ul><li>JP-8 fuel, carbon monoxide </li></ul><ul><li>hydraulic fluid, useful mechanical </li></ul><ul><li>servo fluid, useful mechanical </li></ul><ul><li>Hydraulic fluid, control movement </li></ul>
  60. 60. 58. The TH-67 hydraulic pump is a constant ____, _____ delivery system component providing 600 +/- 25 psi, and _____ GPM flow rate. <ul><li>pressure, variable, 1.9 </li></ul><ul><li>flow, direct, 2.3 </li></ul><ul><li>pressure, flow, 1.2 </li></ul><ul><li>flow, pressure, 1.9 </li></ul>
  61. 61. 59. The purpose of the differential release valve is to reduce ____ ____ ____ when rotor loads are increased due to high “G” maneuvers or flight into turbulence. <ul><li>rotor centrifugal forces </li></ul><ul><li>transmission high speeds </li></ul><ul><li>engine high speeds </li></ul><ul><li>pressure build up </li></ul>
  62. 62. 60. With regard to cyclic input, does the blades position in the plane of rotation matter? <ul><li>No </li></ul><ul><li>Only during forward flight </li></ul><ul><li>Yes, the desired input does not occur until the blade is positioned exactly 90 º earlier in the plane of rotation (phase lag) </li></ul><ul><li>Only during right side flight above 20 knots </li></ul>
  63. 63. 61. What drives the rotating swash plate? <ul><li>The transmission </li></ul><ul><li>The power turbine </li></ul><ul><li>The connection of the collar set and idler lever/link assembly to the rotating swash plate </li></ul><ul><li>The rotating scissors </li></ul>
  64. 64. 62. What is another name for the collar set and idler lever/link assembly? <ul><li>The drag link assembly </li></ul><ul><li>The rotating link assembly </li></ul><ul><li>The rotating swash plate link </li></ul><ul><li>None of the above </li></ul>
  65. 65. 63. What connects the rotating swash plate to the pitch change horn? <ul><li>The pitch control rods (PCR) </li></ul><ul><li>The pitch change tubes </li></ul><ul><li>The swash plate tubes </li></ul><ul><li>The pitch horn tubes </li></ul>
  66. 66. 64. What type of rotor system is used on the TH-67 helicopter? <ul><li>Fully articulated rotor system </li></ul><ul><li>Fully aerobatic rotor system </li></ul><ul><li>Rigid, semi-articulated rotor system </li></ul><ul><li>Semi-rigid, under slung rotor system </li></ul>
  67. 67. 65. How is the rotor system attached to the mast? <ul><li>It is attached to the mast by 4 grade 1172 steel bolts </li></ul><ul><li>The rotor system is attached to the mast by means of bolts, washer, and nuts </li></ul><ul><li>The rotor system is attached to the mast by a splined trunnion </li></ul><ul><li>None of the above </li></ul>
  68. 68. 66. What is the definition of a trunnion? <ul><li>A component that holds things together </li></ul><ul><li>The act of bringing two objects of dissimilar shapes to form one </li></ul><ul><li>A component that allows rotation and tilt </li></ul><ul><li>To turn or to be turned </li></ul>
  69. 69. 67. What is the purpose of the yoke? <ul><li>Attaches the main rotor and main transmission to the hub </li></ul><ul><li>To support the main rotor system and serves as the pitch change axis </li></ul><ul><li>Sends a signal to the cockpit to let the pilot know of exact angle of pitch in the main rotor blades </li></ul><ul><li>A and C </li></ul>
  70. 70. 68. How is the trunnion attached to the yoke? <ul><li>The trunnion is attached to the yoke by pillow blocks </li></ul><ul><li>The trunnion is attached to the yoke by 2 high impact type 117 grade steel bolts </li></ul><ul><li>The trunnion is attached to the yoke by the go/no-go fly wheel assembly </li></ul><ul><li>The trunnion does not attached to the yoke by any means. They are two separate systems independent of one another </li></ul>
  71. 71. 69. What kind of balancing requires lead weights to be added to the blade retention bolt? <ul><li>Trailing edge balancing requires lead weights to be added to the blade retention bolts </li></ul><ul><li>Sprout rigging balancing requires lead weights to be added to the blade retention bolts </li></ul><ul><li>WARNING. Never add weights to the blade retention bolts </li></ul><ul><li>Spanwise (root to tip) balancing requires lead weights to be added to the blade retention bolts </li></ul>
  72. 72. 70. What distributes the centrifugal load from the blade grip to the yoke? <ul><li>The under-slung design of the TH-67 rotor system </li></ul><ul><li>The yoke centrifugal bearings </li></ul><ul><li>Tension torsion straps </li></ul><ul><li>The is no centrifugal force load from the blade grip to the yoke </li></ul>
  73. 73. 71. What structural members make up the main rotor blade? <ul><li>The titanium spar, the chamber, and the trailing edge </li></ul><ul><li>The aluminum spar, the spar closure, and the trailing edge </li></ul><ul><li>The titanium spar, the spar closure, and the trailing edge </li></ul><ul><li>Aluminum, honey comb, and titanium </li></ul>
  74. 74. 72. Weights are added at the factory at the time of manufacturing to control the undesirable twisting associated with asymmetrical airfoils and to preserve favorable aerodynamic characteristics. <ul><li>True </li></ul><ul><li>False </li></ul>
  75. 75. 73. Why does the main rotor blades have a negative 10 º twist? <ul><li>The negative twist is designed to equalize lift during autorotation </li></ul><ul><li>The negative twist is designed to prevent turbulence during high power/high “G” maneuvers </li></ul><ul><li>There is no negative twist on the main rotor blades </li></ul><ul><li>The negative twist is designed to equalize lift along the blade span (length) </li></ul>
  76. 76. 74. The “droop snoot” is known for what aerodynamic characteristics? <ul><li>The “droop snoot” design is noted for a wide thrust margin for maneuverability and high efficiency during forward flight </li></ul><ul><li>The “droop snoot” design is noted for a wide thrust margin for maneuverability and high efficiency during hovering </li></ul><ul><li>The “droop snoot” design is noted for a wide thrust margin for maneuverability and high efficiency during turns </li></ul><ul><li>The “droop snoot” design is noted for a wide thrust margin for maneuverability and high efficiency during autorotation </li></ul>
  77. 77. 75. How many trim tabs are there on the main rotor blade? <ul><li>Two trim-tabs, one for adjusting A+ vibrations and the other one to adjust B+ vibrations </li></ul><ul><li>Just one trim-tab </li></ul><ul><li>Three trim-tabs, one for adjusting the inner blade track, a second for the middle blade track, and a third for the outer blade track </li></ul><ul><li>Two trim-tabs, one for adjusting the inner blade track, and a second trim-tab is used to adjust the outer portion of the blade’s track </li></ul>
  78. 78. 76. What are doublers used for on the main rotor blade? <ul><li>They are applied at the blades root to sustain the shearing force caused by the centrifugal force occurring at the blade retention bolt </li></ul><ul><li>Used to equalize lift along the blade span (length) </li></ul><ul><li>They are designed to stop excessive droop (lower motion of the blade) and conning (upper movement of the blade) </li></ul><ul><li>Doublers are used on the main rotor to reduce main rotor vibrations during slow autorotations </li></ul>
  79. 79. 77. What is the purpose of the flap restraint kit? <ul><li>Its purpose is to limit flapping during autorotations </li></ul><ul><li>Its purpose is to limit flapping during high power maneuvers </li></ul><ul><li>Its purpose is to limit flapping during startup and shutdown </li></ul><ul><li>The is no flap restraint system installed on any under-slung rotor system </li></ul>
  80. 80. 78. At what RPM is flapping limited to 6 º maximum? <ul><li>At 90% N2 and below </li></ul><ul><li>At 97% N2 and below </li></ul><ul><li>At 25% N2 and below </li></ul><ul><li>At 31% N2 and below </li></ul>
  81. 81. 79. At what RPM is the flapping angle no longer limited? <ul><li>Above 31% N2 RPM </li></ul><ul><li>Above 85% N2 RPM </li></ul><ul><li>Above 90% N2 RPM </li></ul><ul><li>Above 25% N2 RPM </li></ul>
  82. 82. 80. How is the tail rotor assembly mounted to the tail rotor output shaft? <ul><li>It is mounted to the tail rotor output shaft by a quick disconnect fitting </li></ul><ul><li>It is mounted to the tail rotor output shaft by a splined trunnion </li></ul><ul><li>It is mounted to the tail rotor output shaft by two crossheads bolts </li></ul><ul><li>It is mounted to the tail rotor output shaft by a spherical bearing </li></ul>
  83. 83. 81. How does the tail rotor system compensates for dissymmetry of lift? <ul><li>The tail rotor assembly compensates for dissymmetry of lift through the chordwise hinge by allowing the blade to feather as it flaps </li></ul><ul><li>The tail rotor assembly compensates for dissymmetry of lift through the trunnion hinge by allowing the blade to feather as it flaps </li></ul><ul><li>The tail rotor assembly compensates for dissymmetry of lift through the crosshead hinge by allowing the blade to feather as it flaps </li></ul><ul><li>The tail rotor assembly compensates for dissymmetry of lift through the delta hinge by allowing the blade to feather as it flaps </li></ul>
  84. 84. 82. What are the washers on the blade bolts used for? <ul><li>They are used for preventing corrosion from dissimilar metals </li></ul><ul><li>They are used for counter weight </li></ul><ul><li>They are used for spanwise balancing </li></ul><ul><li>None of the above </li></ul>
  85. 85. 83. What are the rectangular weights and washers on one end of the trunnion used for? <ul><li>They are used for chordwise balance </li></ul><ul><li>They are used for spanwise balance </li></ul><ul><li>They are used for trailing edge balance </li></ul><ul><li>They are used for leading edge balance </li></ul>
  86. 86. 84. What are the nut, bolt, and washer(s) used for on the dynamic balance wheel? <ul><li>They are used to eliminate high frequency vibrations and to assist in spherical and chordwise balance </li></ul><ul><li>They are used to eliminate high frequency vibrations and to assist in spanwise and trailing edge balance </li></ul><ul><li>They are used to eliminate high frequency vibrations and to assist in spanwise and chordwise balance </li></ul><ul><li>None of the above </li></ul>
  87. 87. 85. Where are the weights that are added at the factory located? <ul><li>They are located on the outboard trailing edge and the blade tip </li></ul><ul><li>They are located on the inboard trailing edge and the leading edge </li></ul><ul><li>They are located on the inboard trailing edge and at the blade tip </li></ul><ul><li>None of the above </li></ul>
  88. 88. 86. What are the washers on the pitch horns used for? <ul><li>They are used as aerodynamic balance during steep turns/high “G” maneuvers </li></ul><ul><li>There are no washers installed on the pitch horn </li></ul><ul><li>They are used as aerodynamic balance to eliminate “pedal creep” </li></ul><ul><li>They are used for spanwise balancing </li></ul>
  89. 89. 87. The TH-67 engine’s rated shaft horsepower is de-rated for _____ ______. <ul><li>100% TQ </li></ul><ul><li>85% TQ </li></ul><ul><li>Transmission compatibility </li></ul><ul><li>Turbine comapatibility </li></ul>
  90. 90. 88. The statement that best describes the TH-67 engine is “Internal combustion gas turbine featuring a ______ ______ ______. <ul><li>free gas turbine </li></ul><ul><li>free power turbine </li></ul><ul><li>reverse combustion chamber </li></ul><ul><li>compressor discharge tube </li></ul>
  91. 91. 89. What are two advantages of a free turbine? <ul><li>Reduces cost throughout the Army, and since is free it does not require calibration every 1,000 hours of flight </li></ul><ul><li>Provides reduced load for starting , and each turbine operates at optimum RPM capacity </li></ul><ul><li>No mechanical connection between the gas turbine thus reducing friction and loss of power, and they can be operated independently of each other </li></ul><ul><li>No cost to the Army, and they are light weight </li></ul>
  92. 92. 90. The purpose of the Air Barrier Filter is to provide clean ______ air to the engine. <ul><li>particle-free </li></ul><ul><li>fresh </li></ul><ul><li>cool </li></ul><ul><li>All of the above </li></ul>
  93. 93. 91. Will the engine air be filtered if the ENG ALT AIR switch is placed in the open position? <ul><li>Yes, but only 39% of the air passing through will be filtered </li></ul><ul><li>No such switch installed in the TH-67 helicopter </li></ul><ul><li>Yes, when the air filtered is bypass, filtered air will still be going into the engine through the secondary filtration system </li></ul><ul><li>No, when the air barrier filter is bypass, unfiltered air will be going into the engine </li></ul>
  94. 94. 92. What indication will the pilot receive when the air barrier filter is blocked/clogged? <ul><li>The FILTER CLOGGED caution light will illuminate </li></ul><ul><li>The HIGH INLET PRESSURE caution light will illuminate </li></ul><ul><li>The LOW INLET PRESSURE caution light will illuminate </li></ul><ul><li>There is no indication sent to the cockpit for this condition </li></ul>
  95. 95. 93. What are the four sections of the model 250-C20J turbine engine? <ul><li>Intake, compressor, combustion, and exhaust section </li></ul><ul><li>Power turbine, combustion chamber, exhaust, and ignition section </li></ul><ul><li>The compressor, power and accessory gearbox, turbine, and combustion section </li></ul><ul><li>The stator vanes, the rotating vanes, the centrifugal stage, and the impeller section </li></ul>
  96. 96. 94. What does the bleed air control valve do? <ul><li>It aids in rapid engine acceleration and helps prevent compressor stalls </li></ul><ul><li>It controls the amount of bleed air needed for cabin/cockpit heating </li></ul><ul><li>It controls bleed air for de-icing of the compressor inlet vane </li></ul><ul><li>Both B and C </li></ul>
  97. 97. 95. What are the five customer bleed air ports on the diffuser scroll? <ul><li>Anti-icing, vent and cap, discharge air, exhaust holes, and PC filter </li></ul><ul><li>The engine anti-ice valve, bleed air control valve, two cabin heat ports, and PC air filter </li></ul><ul><li>Two cabin heat ports, cockpit heat port, and the PC air filter </li></ul><ul><li>None of the above </li></ul>
  98. 98. 96. What is the purpose of the cap on the rear diffuser vent and cap? <ul><li>To increase air pressure on one side of two labyrinth seals as the compressor experiences wear. </li></ul><ul><li>To equalize the high pressure between the diffuser and the compressor section </li></ul><ul><li>To prevent Foreign Object Damage (FOD) from entering the diffuser </li></ul><ul><li>Vents out high pressure from the diffuser and redirects it to the compressor </li></ul>
  99. 99. 97. The compressor consists of how many and what kind of compressor stages? <ul><li>It consists of four axial stages and one centrifugal stage </li></ul><ul><li>It consists of five axial stages and two centrifugal stage </li></ul><ul><li>It consists of five axial stages and one centrifugal stage </li></ul><ul><li>It consists of six axial stages and one centrifugal stage </li></ul>
  100. 100. 98. On a standard day the airs temperature increases to approximately ___ º F by the time it goes through the seventh stage of compression. <ul><li>1270 </li></ul><ul><li>456 </li></ul><ul><li>502 </li></ul><ul><li>520 </li></ul>
  101. 101. 99. What are the only items provided with anti-icing capability? <ul><li>The engine inlet, and the windshield </li></ul><ul><li>The windshield, and the main rotor blade leading edge </li></ul><ul><li>Both, main and tail rotor blades leading edges </li></ul><ul><li>The front support hub and the seven inlet guide vanes </li></ul>
  102. 102. 100. Should the bleed-air control valve be opened or closed on preflight? <ul><li>The bleed-air control valve SHALL be closed on preflight or maintenance action is required </li></ul><ul><li>This valve can not be seen unless parts from the engine are removed during major overhaul to the engine </li></ul><ul><li>The bleed-air valve SHOULD be closed on preflight or maintenance action is required </li></ul><ul><li>The bleed-air valve SHALL be open on preflight or maintenance action is required </li></ul>
  103. 103. 101. When does the spark cease to exist in the combustion section of the engine? <ul><li>When N1 reaches 90% RPM </li></ul><ul><li>When N2 reaches 90% </li></ul><ul><li>When the starter button is released </li></ul><ul><li>The spark never ceases unless there is a failure of the exciter box or engine tachometer generator </li></ul>
  104. 104. 102. What is the temperature of the flame in the combustion section of the engine? <ul><li>Approximately 4500 º F </li></ul><ul><li>Approximately 5500 º F </li></ul><ul><li>Approximately 3500 º F </li></ul><ul><li>Approximately 2500 º F </li></ul>
  105. 105. 103. What is the melting point of titanium? <ul><li>3200 º F </li></ul><ul><li>220 º F </li></ul><ul><li>320 º F </li></ul><ul><li>2200 º F </li></ul>
  106. 106. 104. How much of the compressed air is used for combustion? <ul><li>Approximately 20 to 25% </li></ul><ul><li>Approximately 50 to 60% </li></ul><ul><li>Approximately 70 to 80% </li></ul><ul><li>Approximately 80 to 95% </li></ul>
  107. 107. 105. T or F Approximately 75 to 80% of the air is used to cool and center the combustion flame plus drive the five customer bleed-air accessories. <ul><li>False </li></ul><ul><li>True </li></ul>
  108. 108. 106. What principle takes advantage of impact and reaction forces? <ul><li>Newton’s third law of action and reaction </li></ul><ul><li>Newton’s first law of inertia </li></ul><ul><li>The gas turbine principle </li></ul><ul><li>The action reaction principle </li></ul>
  109. 109. 107. Changes in ____ ______ cause changes in fuel flow. <ul><li>power settings </li></ul><ul><li>wind conditions </li></ul><ul><li>pressure altitude </li></ul><ul><li>high temperature </li></ul>
  110. 110. 108. Changes in fuel flow will cause changes in _______ of the gases entering the turbine rotors. <ul><li>flow </li></ul><ul><li>cooling </li></ul><ul><li>temperature </li></ul><ul><li>expansion </li></ul>
  111. 111. 109. Combustion gases impact the gas producer and the turbine rotors inducing _____________________. <ul><li>rotation of the compressor </li></ul><ul><li>rotation of the accessory gearbox </li></ul><ul><li>rotation of the free wheeling unit </li></ul><ul><li>rotation of the turbine shaft </li></ul>
  112. 112. 110. An increase in expansion rate/velocity induces an increase in _____ that is transmitted through the N2 gear train as measurable _______. <ul><li>air, RPM </li></ul><ul><li>torque, horsepower </li></ul><ul><li>fuel, shaft torque </li></ul><ul><li>fuel, horsepower </li></ul>
  113. 113. 111. Which section of the engine is the primary structural member of the engine? <ul><li>The power and accessory gearbox section </li></ul><ul><li>The compressor section </li></ul><ul><li>The combustion section </li></ul><ul><li>The power turbine section </li></ul>
  114. 114. 112. What is designed to reduce the high RPM required for horsepower development to more practical RPM at the accessory output pads? <ul><li>The reverse flow combustion chamber </li></ul><ul><li>Electrical motors dedicated just to the accessory output pads </li></ul><ul><li>Two separate gear trains (N1 and N2) </li></ul><ul><li>The N1 tachometer and the N2 tachometer </li></ul>
  115. 115. 113. Which section of the engine is driven by the gas producer gear train? <ul><li>The oil cooler section is the only section driven by the N1 gear train </li></ul><ul><li>The combustion section is the only section driven by the N1 gear train </li></ul><ul><li>The turbine section is the only section driven by the N1 gear train </li></ul><ul><li>The compressor section is the only section driven by the N1 gear train </li></ul>
  116. 116. 114. The fuel pump, gas producer fuel control, starter/generator, oil pump, tachometer generator, and the standby generator (only on the IFR configuration) are driven by what gear train? <ul><li>N2 gear train </li></ul><ul><li>N1 gear train </li></ul><ul><li>Both, N1 and N2 gear trains </li></ul><ul><li>None of the above </li></ul>
  117. 117. 115. The freewheeling unit, the torque meter, the governor, and the tachometer generator are driven by what gear train? <ul><li>N1 gear train </li></ul><ul><li>N2 gear train </li></ul><ul><li>Both, N1 and N2 gear trains </li></ul><ul><li>None of the above </li></ul>
  118. 118. 116. The N1 and N2 tachometer generators produce what kind of voltage? <ul><li>Direct Current (DC) voltage </li></ul><ul><li>Alternate Current (AC) voltage </li></ul><ul><li>The N1 DC voltage, and the N2 AC voltage </li></ul><ul><li>The N1 AC voltage, and the N2 DC voltage </li></ul>
  119. 119. 117. The starter portion of the starter/generator is used to “crank” the ____ _____ _____ during the start sequence. <ul><li>N2 gear train </li></ul><ul><li>engine combustion section </li></ul><ul><li>N1 gear train </li></ul><ul><li>accessory gear box </li></ul>
  120. 120. 118. The generator portion of the starter/generator provides ____ ____ voltage to all of the helicopter’s electrical systems plus it re-charges the ___ _____. <ul><li>alternate current, main battery </li></ul><ul><li>direct current, standby battery </li></ul><ul><li>direct current, main battery </li></ul><ul><li>alternate current, standby battery </li></ul>
  121. 121. 119. How are the gas producer fuel control and the governor integrated? <ul><li>They are integrated by pneumatic connections </li></ul><ul><li>They are integrated by mechanical connection </li></ul><ul><li>They are integrated by hydro mechanical connections </li></ul><ul><li>They are integrated electrically </li></ul>
  122. 122. 120. What is the purpose of the burner drain valve? <ul><li>To burn fuel that remains on the outer combustion case </li></ul><ul><li>To drain unburned fuel from the combustion chamber back to the fuel tank </li></ul><ul><li>To allow unburned fuel to drain from the outer combustion case </li></ul><ul><li>None of the above </li></ul>
  123. 123. 121. The purpose of the dual accumulator-double check valve is to ____ _____ ______ from the main rotor system. <ul><li>reduce the vibrations </li></ul><ul><li>dampen torsional vibrations </li></ul><ul><li>maintain CG balance </li></ul><ul><li>None of the above </li></ul>
  124. 124. 122. Where is the combustions gas temperature measured on the C20-J turbine engine? <ul><li>Right before the N1 rotor </li></ul><ul><li>Right after the gas passes by the N2 rotor </li></ul><ul><li>Right in between the N1 and the N2 rotors </li></ul><ul><li>A and B </li></ul>
  125. 125. 123. Where is the engine oil temperature measured? <ul><li>At the combustion chamber #7 bearing solenoid </li></ul><ul><li>It is measured as the oil leaves the bottom of the engine oil reservoir </li></ul><ul><li>It is measured by a “wet” line (direct oil pressure) </li></ul><ul><li>By a “wet” line (direct pressure reading) </li></ul>
  126. 126. 124. How is the engine oil pressure measured? <ul><li>It is measured in PSI by a “dry” line </li></ul><ul><li>It is measured in PSI by the transmission pressure gauge </li></ul><ul><li>It is measured by a “wet” line (direct oil pressure) </li></ul><ul><li>It is measured as it passes through the #2 and #7 bearing </li></ul>
  127. 127. 125. How is the engine torque measured? <ul><li>By a “wet” line (direct pressure reading) </li></ul><ul><li>By the difference in pressure from the sump and the pump </li></ul><ul><li>It is measured by a “wet” line (direct oil pressure) </li></ul><ul><li>None of the above </li></ul>
  128. 128. 126. Which engine bearings are externally lubricated? <ul><li>Bearings 1, 2, 5, and 8 </li></ul><ul><li>Bearings 5, 6, 7, and 8 </li></ul><ul><li>Bearings 2, 2 ½, 6, 7, and 8 </li></ul><ul><li>Bearings 1, 6, 7, and 8 </li></ul>
  129. 129. 127. How many engine oil chip detectors will activate the ENG Chip caution light? <ul><li>One (the accessory section chip detector) </li></ul><ul><li>One (the temp/chip detector) </li></ul><ul><li>Two ( the #1 and #2 chip detectors) </li></ul><ul><li>Two (the sump and the pump chip detectors) </li></ul>
  130. 130. 128. The auxiliary oil filter has a “pop-up” feature that activates at __ PSID. <ul><li>17 </li></ul><ul><li>10 </li></ul><ul><li>7 </li></ul><ul><li>40 </li></ul>
  131. 131. 129. After completing lubrication, oil is scavenged into a sump below the number __ and __ bearings and at the bottom of the gear case. <ul><li>2, 2 ½ </li></ul><ul><li>3, 4 </li></ul><ul><li>5, 6 </li></ul><ul><li>6, 7 </li></ul>
  132. 132. 130. How many engine oil bypasses are there? <ul><li>There are 4 bypasses. Auxiliary oil filter (10 PSID), oil cooler (thermal bypass below 81 º C or 178 º F), oil cooler (40 PSI clogged oil cooler), and internal oil filter (150 PSID) </li></ul><ul><li>There are 4 bypasses. Auxiliary oil filter (7 PSID), oil cooler (thermal bypass below 81 º C or 178 º F), oil cooler (40 PSI clogged oil cooler), and internal oil filter (105 PSID) </li></ul><ul><li>There are 4 bypasses. Auxiliary oil filter (10 PSID), oil cooler (thermal bypass below 81 º C or 178 º F), oil cooler (40 PSI clogged oil cooler), and internal oil filter (105 PSID) </li></ul><ul><li>There are 4 bypasses. Auxiliary oil filter (10 PSID), oil cooler (thermal bypass below 81 º F ), oil cooler (40 PSI clogged oil cooler), and internal oil filter (105 PSID) </li></ul>
  133. 133. 131. How many “wet” lines are there associated with the engine oil system? <ul><li>Three (the engine oil pressure, and torque meter gauges, and the transmission oil pressure gauge) </li></ul><ul><li>Two (the engine oil pressure, and the transmission oil pressure gauge) </li></ul><ul><li>Two (the engine oil pressure, and the torque meter gauges) </li></ul><ul><li>Three ( transmission oil and pressure gauges, and the torque meter gauge) </li></ul>
  134. 134. 132. Is defined as a decrease in N2 RPM that exists between the time a demand for power is made and the time that power is delivered? <ul><li>Spike knock </li></ul><ul><li>Mast bumping </li></ul><ul><li>Droop </li></ul><ul><li>Flapping stop </li></ul>
  135. 135. 133. Is droop allowed to exist? <ul><li>No, INTENTIONAL USE IS PROHIBITED </li></ul><ul><li>Yes, 5 minute limit </li></ul><ul><li>Only momentarily, otherwise rotor RPM may become critically low </li></ul><ul><li>Yes, but rotor RPM must be at 107% RPM to compensate for droop </li></ul>
  136. 136. 134. How is droop compensated for? <ul><li>By lowering the collective, and turning the engine anti-ice and heater switches off </li></ul><ul><li>Once droop is encounter you must wait until the aircraft recovers from it </li></ul><ul><li>Through mechanical linkages (collective stick to governor lever), electrical connections (governor increase/decrease switch and linear actuator motor), and a pneumatic signal between the N2 governor and the gas producer fuel control passing through the dual accumulators and double check valve </li></ul><ul><li>By lowering the collective and maintaining 107% max RPM </li></ul>
  137. 137. 135. Why is the engine mounted horizontally behind the transmission <ul><li>To simplify the drive system, improve the air intake/exhaust arrangement, and to reduce cabin noise </li></ul><ul><li>All helicopter must have the engine horizontally mounted for weight and balance purposes </li></ul><ul><li>By the engine being mounted horizontally it will improve the autorotational capability by 40% </li></ul><ul><li>For no particular reason, it’s just the way the engineers wanted it mounted </li></ul>
  138. 138. 136. How are three bipod mounts used to secure the engine? <ul><li>Semi-rigid </li></ul><ul><li>Flexible for vibration reduction </li></ul><ul><li>Rigidly </li></ul><ul><li>None of the above </li></ul>

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