BIMOTOR

The nose gear is steerable through a ____ degree are either side of center by use a combination of full ruder pedal travel and brake. a)30. b)21. c)45. d)27.

The Vmca is :_. a) 66kts. b) 64kts. c) 60kts. d) 68kts.

4. The wing span of the Piper Seneca III is: a)11.85m. b)11.85inch. c)9.87m. d)9.87inch.

5. What is the maximum time allowed with take-off power 220 rated BHP at 2800 RPM?. a) 2min. b) 3min. c) 5min. d) 7min.

What is the critical engine in this aircraft?. a)Right. c) Both. b)Left. d)Neither.

6. The maximum power of the Seneca’s engine is: The landing gear is designed to extend even in the event of failure, should the hydraulic system fail for any reason,. a) another hydraulic system will allow the gear to extend. b) gravity will allow the gear to extend. c) electricity system will allow the gear to extend. d) pneumatic system will allow the gear to extend.

7. The engine is: a) Six cylinders, horizontally opposed, oil cooled. b) Four cylinders, horizontally opposed, air cooled. c) Six cylinders, horizontally opposed, air cooled. d) Four cylinders, horizontally opposed, liquid cooled.

8. The propellers are: a) Hartzell brand, fixed pitch and full feathering. b) McCauley brand, constant speed and full feathering. c) Hartzell brand, fixed pitch and not feathering. d) Hartzell brand, constant speed and full feathering.

9. The usable fuel capacity of this aircraft is: a) 128 U.S. Gal. b) 123 Liters. c) 123 U.S. Gal. d) None of the above.

10. The maximum weight with we can carry in the forward cargo hold is: a) 100 lbs. b) 100 kg. c) 200 lbs. d) There is no forward cargo hold.

11. The maximum speeds for the landing gear operation are: a) Retracted before 138 KIAS and extended before 140 KIAS. b) Retracted before 130 KIAS and extended before 108 KIAS. c) Retracted before 108 KIAS and extended before 130 KIAS. d) Retracted before 109 KIAS and extended before 139 KIAS.

12. The red line of the never exceed speed is at: a) 203 KIAS. b) 230 KIAS. c) 205 KIAS. d) 250 KIAS.

13. The white arc of normal operation speed is found between: a) 67 and 116 Kts. b) 80 and 170 Kts. c) 64 and 115 kts. d) 40 and 120 kts.

14. The best rate of climb speed with one engine inoperative is: a) 120 kts. b) 100 kts. c) 92 kts. d) 88 kts.

15. Pitch is controlled by: a) Oil pressure sends a propeller toward the high RPM or unfeather position and nitrogen pressure sends a propeller toward the low RPM or feather position and also prevents propeller overspeeding. b) Nitrogen pressure sends a propeller toward the high RPM or unfeather position and oil pressure sends a propeller toward the low RPM or feather position and also prevents propeller overspeeding. c) Only oil pressure is used. d) Only nitrogen pressure is used.

16. Which is the maximum RPM of the Seneca’s engine: a) 2575 RPM. b) 2800 RPM. c) 2850 RPM. d) 2950 RPM.

17. The E.G.T. indicates: a) Engine Gyro Torque. b) Electrical Generator. c) Exhaust Gas Temperature. d) Engine Government Thrust.

18. What is the White Arc?. a) Full Flap Operating Range. b) Normal Operating Range. c) Operations must be conducted with caution and only in smooth air. d) One Engine Inoperative Best Rate of Climb Speed.

19. One Engine Inoperative Air Minimum Control Speed is _____. a) 87KIAS. b) 66KIAS. c) 85KIAS. d) 65KIAS.

20. The Landing Gear System is driven: a) Electrically. b) Electrically powered hydraulic pump. c) Hydraulically by a pump driven by the engine. d) Hydraulically in a normal operation and electrically in emergency mode.

21. Gear extension or rectraction normally takes: a) 4 to 5 seconds. b) 5 to 6 seconds. c) 6 to 7 seconds. d) 7 to 8 seconds.

22. Emergency gear extension must not be attempted at airspeed in excess of: a) 85KIAS. b) 90KIAS. c) 95 KIAS. d) 80KIAS.

23. The fuel selector set at the position of X-FEED gives: a) Fuel from the opposite tank to the proper tank. b) Fuel from the opposite tank to the proper engine. c) Fuel to the opposite engine from the proper tank. d) None of the above.

24. The electrical system consists of: a) 2 alternators which provide 65 amperes and 2 solid state voltage regulators. b) Like the above but the alternators provide 30 amperes each one. c) Like the above but there is only one overvoltage relay. d) Like the option “A” but we have two batteries, one for normal operation and the other one for emergency.

25. The vacuum system consists of: a) A vacuum pump per engine. b) A vacuum pump for every instrument which needs for its supply. c) An electrical vacuum pump. d) Two electrical vacuum pumps.

26. How many tanks does the Seneca have?. a) 3. b) 4. c) 5. d) 6.

27. The pitot-static system consists of: a) A pitot tube on the left wing and two static vents on each side of the fuselage. b) A pitot tube on the left wing and static vent on the same pitot tube. c) A pitot tube on the right and a static vent situated in the cabin. d) A pitot tube on the left wing, an static vent on the same pitot tube and an alternate static inside the cabin situated on the left side of the cockpit.

28. The blue line of the air speed indicator, shows: a) The maximum speed for flap setting. b) The best rate of climb with one engine out (Vyse). c) The minimum control speed. d) The maneuver speed.

29. What is the maximum charge of the alternator?. a) 60 A. b) 65 A. c) 35 A. d) 30 A.

30. How many drain points has the Seneca got?. a) 2. b) 6. c) 8. d) 4.

the engines of the seneca are. lycoming. continental. rolls royce. rotax.

max power of the engine´s seneca. 170. 180. 200. 220.

pitch is controlled by. oil pressure send a propeller toward the high rpm or unfeather position. oil pressure sends a propeller toward the low rpm or feather position and also prevents propeller overspeeding. a and b are correct. only a) is correct.

MTOM. 4407 KG. 4750 LBS. 4007 KG. 4007 LBS.

the green arc is found between. 67 and 166. 80 and 170. 60 and 180. 40 and 190.

a micro switch in the throttle quadrant avtivates the gear warning horn under the following conditions (REVISAR). the gear is locked down and the manifold pressure has fallen below 14 inches or either one or both engines. the gear selector is inthe úp´position when the airplane is on the ground. a and b. b is correct.