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TH-67 Systems

TH-67 Systems. Study Guide (General Description, Flight Controls and Hydraulics, Rotors, and Power Plant). 1. Define the term WARNING. An operating procedure, practice, etc., which if not strictly observed could result in damage to or destruction of equipment. A mandatory procedure

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TH-67 Systems

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  1. TH-67 Systems Study Guide (General Description, Flight Controls and Hydraulics, Rotors, and Power Plant)

  2. 1. Define the term WARNING • An operating procedure, practice, etc., which if not strictly observed could result in damage to or destruction of equipment. • A mandatory procedure • An operating procedure, practice, etc., which if not correctly followed could result in personal injury or loss of life. • Indicated futurity

  3. 2. Define the term CAUTION • An operating procedure, condition, etc., which is essential to highlight. • An operating procedure, practice, etc., which if not strictly observed could result in damage to or destruction of equipment. • An operating procedure, practice, etc., which if not correctly followed could result in personal injury or loss of life. • Indicates futurity

  4. 3. Define NOTE • A mandatory procedure • Recommended or preferred, not mandatory. • Indicates futurity • An operating procedure, condition, etc., which is essential to highlight.

  5. 4. Define the term SHALL • Indicated futurity • A mandatory procedure • An optional procedure • Recommended or preferred, not mandatory

  6. 5. Define the term SHOULD • Recommended or preferred, not mandatory • An optional procedure • A mandatory procedure • An operating procedure, condition, etc., which is essential to highlight

  7. 6. Define the terms MAY or NEED NOT • Indicated futurity • A mandatory procedure • A condition that you may do or not • An optional procedure

  8. 7. Define the term WILL • An optional procedure • Indicates futurity • A mandatory procedure • A procedure that will be done

  9. 8. The three sections of the TH-67 fuselage are the _____, _______, and the _______ section. • cockpit, cabin, and aft boom • front, intermediate, and back tail • forward, intermediate, and tail boom • cockpit, cabin, and tail

  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. • direct, indirect • pressure, kinetic • impact (ram), static • direct, static

  11. 10. The IFR configuration has __ ______ pitot/static systems. • 4 separate • 3 individual • 2 independent • 2 individual

  12. 11. The TH-67 ____ light, located on the aircraft nose provides a 450 watt lamp in an extendable and slewable mount. • landing • position • collision • search

  13. 12. The TH-67 ____ light, located on the aircraft nose provides a 250 watt lamp in a fixed mount. • landing • search • position • collision

  14. 13. How many switches are used to control the search light in the NVG mode on the A+ configuration? • 2, one for selecting IR light, and one to turn it on. • 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. • 3, one to select the IR light, one to turn the light on, and one to slew the search light to the desired position. • 2, one on/off switch, and one to select IR.

  15. 14. What does the term semi-monocoque mean? • The skin of the aircraft provides all of the structural strength • The aircraft skin provides none of the structural strength • The aircraft skin provides some of the structural strength • None of the above

  16. 15. The TH-67 intermediate section uses a ____ type of construction. • semi-rigid • semi-flex • semi-monocoque • monocoque

  17. 16. Which section of the aircraft contains the engine? A. The forward section B. The cabin section C. The engine/transmission section D. The intermediate section

  18. 17. The TH-67 tail boom section uses ___ ______ type of construction. • semi monocoque • partial monocoque • fully monocoque • semi rigid

  19. 18. State the purpose of the vertical fin. • Provides vertical stability on the x-axis • The vertical fin, being displaced (canted) 5 ½ degrees to the right thus reducing the tail rotor thrust requirements in forward flight • Off-loads the tail rotor between 80 and 100 knots • Provides vertical stability on the yaw axis

  20. State the purpose of the horizontal stabilizer. 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. B. Provides pitch (up and down) about the lateral axis C. Provides horizontal control of the aircraft during low “G” maneuvers. D. None of the above

  21. 19. At what airspeed is the tail rotor fully off-loaded in forward flight? • Between 110 and 130 knots • Between 90 and 120 knots • At 100 knots • Between 100 and 110 knots

  22. 20. The nomenclature of the TH-67 power plant is the model _______. • T700-GE-401C • JP-WD40 • PW-123-J • 250-C20J

  23. 21. State the maximum torque available (MAX TQ AVAIL). • 107% TQ for 15 seconds max • 100% TQ for 5 minutes max • >85% to 100% for 5 minutes max • 100% TQ for 5 seconds max

  24. 22. State the maximum continuous power (TQ AVAIL CONT) of the TH-67 power plant. • 85% TQ (270 SHP) no time limit • 85% TQ (270 SHP) take-off power range 5 minute limit • >85% to 100% TQ maximum • 100% TQ no time limit

  25. 23. Can the maximum transient power setting (110% TQ) be used intentionally? • Yes, 5 minutes limit • Yes, 5 seconds limit • No, only when executing high ‘G’ maneuvers • No, intentional use is prohibited

  26. 24. State the diameter of the TH-67 main rotor. • 52’ 4” • 42’ 4” • 33’ 4” • 44’ 3”

  27. 25. What type of airfoil is the main rotor blade? • A honey comb airfoil • A symmetrical airfoil • An asymmetrical airfoil • None of the above

  28. 26. How many degrees of twist are there in the main rotor blade? • A positive 10 degrees • A negative 5 degrees • A positive 5 degrees • A negative 10 degrees

  29. 27. State the tail rotor diameter. • 5’ 10” • 4’ 5” • 5’ 5” • 8’ 5”

  30. 28. How many degrees of pitch are in the tail rotor with full left pedals applied? • 25 degrees • 23 degrees • 17 degrees • 21 degrees

  31. 29. State the TH-67 Vne • 122 knots • 78 knots • 130 knots • 100 knots

  32. 29. State the maximum airspeed limitation with >85 to 100% TQ applied. • 78 knots • 110 knots • 80 knots • 122 knots

  33. 31. State the minimum rate of descent airspeed in autorotation. A. 50 knots @ 394 RPM (100% rotor RPM) B. 69 knots @ 394 RPM (100% rotor RPM) C. 52 knots @ 394 RPM (100% rotor RPM) D. 60 knots @ 394 RPM (100% rotor RPM)

  34. 32. State the maximum glide distance airspeed in autorotation. • 69 knots @ 394 RPM (100% rotor RPM) • 79 knots @ 394 RPM (100% rotor RPM) • 52 knots @ 394 RPM (100% rotor RPM) • 60 knots @ 394 RPM (100% rotor RPM)

  35. 33. State the minimum crew restriction VFR and IFR. • VFR minimum 1 pilot, IFR minimum 1 pilot and 1 observer • VFR minimum 2 pilots, IFR minimum 1 pilot • VFR minimum 1 pilot, IFR minimum 2 pilots • VFR minimum 1 student, IFR minimum 1 student and 1 pilot

  36. 34. State the fuel capacity of the TH-67 fuel cell. • 69.4 U.S. gallons total; 64.2 U.S. gallons useable; 2.3 U.S. gallons unusable • 81.4 U.S. gallons total; 64.2 U.S. gallons useable; 1.5 U.S. gallons unusable • 69.4 U.S. gallons total; 68.2 U.S. gallons useable; 1.3 U.S. gallons unusable • 84.1 U.S. gallons total; 82.6 U.S. gallons useable; 1.5 U.S. gallons unusable

  37. 35. Why must the engine oil system be drained and refilled if transmission and engine oils are intermixed? • To prevent chemical reaction • To prevent damage to the engine oil seals • If the two are mixed they become very flammable • To prevent damage to the transmission

  38. 36. In a conventional helicopter, what are the three basic flight controls that are used to maneuver the aircraft? • Throttle, stick, rudder • Cyclic, stick, collective • Cyclic, collective, tail rotor (anti-torque) pedals • Stick, elevator, vertical fin

  39. 37. In a conventional helicopter, which flight control directs the total lift/thrust of the main rotor system? • The collective • The stick • The pedals • The cyclic

  40. 38. Which conventional helicopter flight control will input a pitch change to all main rotor blades simultaneously regardless of the blades position? • Cyclic • Rudder • Collective • Stick

  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. • The torque force will cause the fuselage of the aircraft to rotate in the same direction of the main rotor • The torque force will cause the fuselage of the aircraft to rotate in the opposite direction of the main rotor • No effect is observed since rotor torque and fuselage torque will be equalized • None of the above

  42. 40. State the primary purpose of the tail rotor system in a conventional helicopter. • Provides directional control • Yaws the aircraft • To counter-act the torque effects of the main rotor • Provides right and left inputs on a hover

  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. • Cyclic pedals • Stick pedals • Tail rotor • A and B

  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 ______. • intermixing bellcrank, coordinated • self adjusting controls, manual • intermixing push rods, coordinated • self input controls, manual

  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? • Nothing, there is no difference with both or just one cyclic stick installed/removed • The reduced load on the balance spring will cause the pilot’s cyclic stick to creep aft slightly • If this situation is encountered you must not go flying do to lack of controls on the aircraft • You must maintain right cyclic input to counteract for the missing copilot’s cyclic stick

  46. 44. Where is the cyclic friction knob located? • Right on the base of the copilot’s cyclic stick • There is not such thing installed in the TH-67 helicopter • In between the pilot and copilot seat • Left of the base on the pilot’s cyclic stick

  47. 45. How much preload is on the cyclic system with the aircraft running and the hydraulics on? • 2 to 3 pounds preload • 1 to 1 ½ pounds preload • 2 ½ to 4 pounds preload • ½ to 1 pound preload

  48. 46. Which aircraft configuration has the force trim system? • VFR only • IFR only • A+ only • All of the above

  49. 47. What switches are located on the pilot’s collective stick control head? • On/off switch, landing light, fuel start • Search light switches, landing light, governor RPM increase/decrease, and the starter button • There is no switches on the pilot’s collective stick; all switches are located on the copilot’s collective stick • Fuel valve switch, landing light, starter button, and hover button

  50. 48. Where is the collective friction located? • It is located on the right of the copilot’s collective stick base • Right behind the pilot’s anti-torque pedals • It is located on the left of the pilot’s collective stick base • No such thing installed in the TH-67 helicopter

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