Piper Seneca III PA-34 220T Questions PDF

PIPER SENECA III PA-34 220T QUESTIONS BY CAPT JP SHARMA Note: The number in the parenthesis refers to the page number of the POH where the answer is to be found. 1. What is the one engine inoperative air minimum control speed? 66 KTS (called VMCA)...

PIPER SENECA III PA-34 220T QUESTIONS BY CAPT JP SHARMA Note: The number in the parenthesis refers to the page number of the POH where the answer is to be found. 1. What is the one engine inoperative air minimum control speed? 66 KTS (called VMCA) (3.2) 2. What is the one engine inoperative best rate of climb speed? 92 KTS (called VYSE) (3.2) 3. Action in case of engine failure in flight when speed is below 66 KTS: Apply rudder towards operative engine to maintain directional control and throttle should be retarded to stop yaw forces produced by inoperative engine. (3.25) 4. Which of the following is incorrect? The propeller can be feathered only while engine is rotating above 600 RPM. (7.5) 5. When will the landing gear warning sound? At low throttle setting when gear is not down and locked. (7.6 and 7.12) 6. How to execute manual extension of landing gear in flight? Maintain speed below 85 KIAS, landing gear selector switch to gear down and pull the emergency gear extension knob. (7.13) 7. What is the total fuel tank capacity of the standard tank? 98 US Gallons (2.7) 8. What is the usable fuel tank capacity of the standard tank? 93 US Gallons (2.7) 1 9. Action in case of engine failure during take-off when speed is 82 KTS and insufficient runway available to stop: Close throttle immediately, apply maximum brakes, switch off battery, switch off fuel selector and continue straight ahead to stop. (3.22) 10. What is the type of battery? 24 Volt, 65 Amp (19 AH) (7.23) 11. What is the type of alternator? 2 x 28 Volt 60 Amperes (7.23) 12. What are the engine controls? Throttle lever, Mixture control lever and Propeller control lever (7.6) 13. What should be the immediate action to recover from an unintentional spin? Retard throttle to idle, apply full opposite rudder, control wheel forward and aileron neutral. (3.18) 14. Nose landing gear extension and down locking is assisted by: Aerodynamic load and springs. (7.11) 15. In the event of propeller over speed, a pilot should: Retard throttle to full aft and also move the propeller control to full decrease RPM (3.19) 16. Nose landing gear is steerable: 27° either side of centre. (7.14) 17. The centre of gravity (rearward) limit for 3400 Kg is: 94.6” (2.6) 18. One engine failure can be identified by: Loss of thrust and yawing towards inoperative engine. (3.2) 2 19. The normal CHT range is: 240° to 460° F (2.5) 20. The normal EGT range is: 1200° to 1525° F (2.5) 21. The design maneuvering speed is: 140 KIAS and it decreases with lighter weight of the aircraft. (2.2) 22. The main gear tyre pressure is: 55 PSI (8.15) 23. The nose gear tyre pressure is: 40 PSI (8.15) 24. The maximum flaps extended speed (VFE) is: 115 KIAS (2.2) 25. The maximum landing gear extended speed (VLE) is: 130 KIAS (2.2) 26. The maximum landing gear operating speed (VLO) is: Extension:130 KIAS, Retraction: 108 KIAS (2.2) 27. The one engine inoperative air minimum control speed (VMCA) is: 66 KIAS (2.2) 28. The never exceed speed (VNE) is: 205 KIAS (2.1) 29. The maximum structural cruising speed (VNO) is: 166 KIAS (2.1) 30. The maximum take-off RPM is: 2800 RPM for 5 minutes (2.3) 3 31. The type of engine is:- Six cylinders, direct drive, horizontally opposed, air cooled (1.3) 32. What is used for moving the propeller from feather (coarse) to un- feather (fine)? Oil pressure (7.4) 33. What is used for moving the propeller from un-feather (fine) to feather (coarse)? Nitrogen (7.4) 34. From which drain point is contaminated fuel drained? The drains in each gascolator, the cross feed drains and fuel quick drains. (7.21) 35. The engine prime time is:- 3 seconds and it varies according to ambient temperature(4.31 and fig 4.3 on 4.30) 36. Hydraulic pressure for the landing gear is provided by:- Electrically powered, reversible hydraulic pump. (7.8) 37. Shimming of nose landing gear is prevented by:- Centering spring. (7.14) 38. The type of brake system used is:- Separate hydraulic reservoir, 2 single disc, double puck brake assemblies, one on each main gear. (7.15) 39. The landing gear is held in retracted position by:- Hydraulic pressure (7.13) 40. The purpose of Squat Switch in landing gear is:- To prevent gear retraction on ground. It is located in left main gear. (7.12) 4 41. What is the altitude limit for operation of Combustion Heater? Operation of Combustion Heater above 25000 feet is not approved. (2.8) 42. How many Fuel Tank Vents are provided? Two Fuel Tank Vents one under each wing. (7.18) 43. The datum is:- 78.4” ahead of wing leading edge at the inboard edge of inboard fuel tank. (6.4) 44. How is the magnetic drop carried out:- At 2000 RPM, maximum drop 150 RPM, maximum difference 50 RPM (4.14) 45. The correct statement about Combustion Heater is:- In the event of Combustion Heater overheat, the fuel, air and ignition to the Heater is automatically cut off. (3.37) 46. The starter cranking is limited to:- 30 seconds. (4.9) 47. What type of trim tab is provided in the stabilator? The stabilator incorporates an anti-servo tab that moves in the same direction as the stabilator. (7.2) 48. The type of air filter used is:- Paper element type. (8.8) 49. Upper red radial line signifies:- Never exceed speed (VNE) 205 KIAS (2.3) 50. Blue radial line signifies:- One engine inoperative best rate of climb speed (VYSE) 92 KIAS. (2.3) 51. Yellow arc signifies:- Caution range of speed (may be used in smooth air only) (2.3) 5 52. Oil viscosity recommended is:- Below 40° F: 1065 (Aviation grade), SAE 30 Above 40° F: 1100 (Aviation grade), SAE 50 (1.5) 53. Lower red radial line signifies:- One engine inoperative air minimum control speed (VMCA) and it is 66 KIAS (2.3) 54. The wing loading is:- 22.8 Lbs/Sq Ft (1.5) 55. The power loading is: 10.8 Lbs/ HP (1.5) 56. When does stall warning sound? 5 to 10 knots before the actual stall and mild airframe buffeting and gentle pitching may precede the stall. (7.50) 57. The type of stall warning is:- Continuous horn. It is different from the landing gear warning horn which beeps at 90 cycles/second (7.50) 58. How is the aircraft towed? Towing can be done using nose wheel steering bar which is stowed in the baggage compartment or by power equipment that will not damage or excessively strain the nose gear steering assembly. Do not tow aeroplane when controls are secured. (8.5) 59. The propeller type is:- Three blade, constant speed, hydraulically activated, controllable pitch and full feathering Mc Cauley, directly connected to crank shaft. (1.4) 60. The Fuel selector during single engine operations should be:- Selector for operating engine: X-FEED Selector for inoperative engine: OFF (3.32) 6 61. Can the alternate air be used on ground? Alternate air should not be used on ground. (7.3) 62. Basic empty weight is: The standard empty weight plus optional equipment. In other words the basic empty weight is the aircraft weight plus unusable fuel plus full oil plus unusable fluids (1.12) 63. Continuous ground operation limitation above 32” of Hg is: Between 2000 and 2200 RPM avoid continuous ground operation (for 2 blade propeller only) above manifold pressure 32” of Hg. (2.11) 64. Continuous ground operation limitation in X-wind and tail wind over 10 KTS is: Between 1700 and 2100 RPM avoid continuous ground operation in X-wind and tail wind over 10 KTS. (2.11) 65. Action to be taken in case of propeller over speed (caused by propeller governor malfunction) which allows the propeller blades to rotate at full low pitch is: Reduce throttle, propeller to full decrease RPM(do not feather), check for control availability, reduce airspeed and throttle to maintain 2600 RPM. (3.37) 66. How is alternate air obtained for engine? Automatic alternate air door opens if primary air source is blocked but alternate air is unfiltered and should not be used for ground operations. (7.3 and 7.6) 67. In case of engine failure during take-off, speed more than 85 KTS and there is insufficient runway to stop, the pilot should:- Maintain directional control, close throttle immediately, land if airborne, stop straight ahead, and apply brakes as required. (3.3) 7 68. What is the feathering procedure: Throttle-retard to verify, propeller- feather at more than 800 RPM, mixture- idle cutoff, cowl flaps- close, alternator- off, fuel selector- off, electrical load- reduce and cross feed- as required. (3.2) 69. Emergency gear extension is aided by : Aerodynamic forces and springs. (7.11) 70. Engine operating limits are: 40” Hg MAP/2800 RPM/220 BHP for 5 minutes. (2.3) 71. Yellow arc on tachometer indicates: 2600 to 2800 RPM (take-off RPM for 5 minutes). (2.5) 72. Relationship of prime time and ambient temperature is: Prime time increases if ambient temperature decreases. (4.30 fig. 4.3) 73. Maximum drop allowed during feathering check is: 300 RPM. (4.36) 74. Normal take-off procedure is: RPM 2800 before releasing brakes that is less than full throttle, 40”of Hg MAP. (4.38) 75. Flap position for short-field take-off is: 25°. (4.39) 76. What will happen to landing gear in case of hydraulic failure? Landing gear will free fall. (7.13) 77. What is the propeller setting on final? Full forward for a possible go around. (4.45) 8 78. The vacuum system is: One vacuum pump for each engine, plumbing and regulating equipment. (7.32) 79. Oxygen system malfunction is indicated by: Red pellets are visible. (9.10) 80. Propeller setting for taxi is: High RPM low pitch. (8.5) 81. What happens by pulling the emergency gear extension knob? Releases hydraulic pressure. (7.13) 82. Auxiliary fuel pump is provided to: Supply fuel in case of failure of engine driven pump and for vapour suppression. (7.18) 83. Minimum steady flight speed at which aeroplane is controllable in landing configuration is called:- Stall speed VSO. (1.8) 84. Maximum landing weight is:- 4513 Lbs. (2.6) 85. The corrected noise level with two blade-propeller and with three blade-propeller respectively is:- 71.4 dB(A) and 74.2 dB(A) 86. when does LO BUS voltage annunciator illuminate? Any time total BUS voltage falls below approximately 25 volt DC. (3.16) 87. If both suction pumps fail:- Artificial horizon and directional gyro will not work, turn indicator will work and de-icing boots will not work. (7.40) & (9.20) 9 88. Ground check of pitot heat must be limited to:- 3 minutes. (4.7) 89. The speed at which maximum height is gained for a given distance travelled is called:- Best angle of climb speed(VX). (1.9) 10