Beechcraft BE-55 _ BE-58 Baron — BE55_TEST_a NOT FOR FLIGHT — source fidelity: unreviewed | operational review: none | completeness: full Source: Beechcraft/BE-55 _ BE-58 Baron/BE55_TEST_a.txt Rights: licensed Checklist hash: 7dcb3539fed29b93d9469645cd187e286e20890e253e743f94a39c61c1fa28be Verify against the aircraft's own approved documentation before use. ======================================================================== OPEN BOOK QUESTIONS ------------------- THE FOLLOWING QUESTIONS ARE OPEN BOOK ** NOTE: Refer to the Army T-42A Operator’s Manual [ ] 1. If the pilot’s brakes fail, the aircraft may be slowed using the parking brake. A. True. The aircraft has two independent brake systems as a backup for just such an emergency. B. False. Setting or pulling the parking brake knob does not pressurize the brake system, but closes the valve in the lines so that the hydraulic pressure built up by pressing the brake pedals is retained.. [ ] 2. Should the induction air filter become blocked by ice, dust, water, etc., a spring-loaded door will automatically open providing an alternate source of intake air. A. True. If the normal air intake is sufficiently blocked, the partial vacuum created will open the spring loaded door. B. False. The pilot must manually select the alternate air source by positioning the appropriate alternate air control lever, on the lower part of the throttle quadrant, to the ON position. [ ] 3. In the event of a total failure of the aircraft’s electrical system which of the following engine instruments will still operate normally? More than one answer may be correct A. Tachometer. B. Manifold pressure gauge. C. Oil pressure gauge. D. Oil and cylinder head temperature gauges. [ ] 4. Fuel boost pumps in the Baron _____________________ A. are not normally used for takeoffs, landings, and in flight B. are used for priming, for failure of engine driven pumps, or to correct fuel pressure fluctuations. C. can draw fuel from any tank. D. All of the above. [ ] 5. The two main fuel tanks in each wing leading edge contain _______ usable and the two auxiliary tanks in the wing panels outboard of each engine nacelle contain ________ usable for a total useable fuel capacity of ________: A. 50 gal; 21 gal; 142 gal B. 40 gal; 31 gal; 142 gal C. 40 gal; 28 gal; 136 gal D. 37 gal; 31 gal; 136 gal [ ] 6. If one engine fails in flight, which fuel tanks are available to feed the operating engine? A. Main only on good engine side; main and aux on dead engine side. B. Main and aux on good engine side; aux only on dead engine side. C. Main and aux on good engine side; main only on dead engine side. D. Main and aux on good engine side; main and aux on dead engine side. [ ] 7. When may the fuel selectors be switched to the auxiliary tanks after takeoff? A. Only during level flight. B. Only after 60 minutes of fuel have been used from the main tanks to allow room for the fuel vapors being returned from the carburetor. C. The auxiliary tanks should only be used after the main tanks have been depleted. D. The auxilary tanks should only be used after the main tanks are half empty to maintain the airplane within its weight and balance limits. [ ] 8. Illumination of the yellow battery charge rate caution light ________. A. indicates a battery overcharge rate exists B. is normal after engine start, but should extinguish within two to five minutes. C. may indicate a battery malfunction if this occurs in cruise flight. The emergency checklist should be followed. D. All of the above. [ ] 9. Each alternator switch has three positions: OFF, ON, and RE-EXC. The RE- EXC position _________. A. Is used when the battery switch has been turned OFF because of a battery malfunction and the alternators have dropped off line. B. Is used to energize the alternators after normal engine starts. C. Is used to re-excite the alternator field if both alternators are off-line and the battery has deteriorated below the level required to re-establish normal alternator operation.. D. Either A or C [ ] 10. If the taxi light is inoperative, the landing lights may be used without restriction for ground operations. A. True. There is no restriction on the use of the landing lights while on the ground. B. False. The use of landing lights on the ground must be minimized since the flow of cooling air over the light shields is insufficient to prevent overheating. [ ] 11. A minimum run takeoff followed by an obstacle clearance climb as described in the T-42 flight manual, _______. A. is a contingency maneuver performed below VMCA and below power-off stall speed. B. will result in a loss of aircraft control and probably a spin if an engine failure is experienced on takeoff before VYSE has been attained. C. is not an authorized maneuver for Langley Aero Club members (with or without an instructor on board). D. All of the above. [ ] 12. If the fuel pressure on an engine drops below normal operating limits or a fuel leak exists or is suspected, the throttle should be retarded to idle and the engine shut down immediately. A. True. It is important to retard the throttle to minimize the amount of fuel being pulled into the engine compartment. B. False. Because of the danger of fire when the airflow through the engine nacelle is changed, under no conditions should the throttle be retarded when a fuel leak is even suspected. [ ] 13. You are planning to takeoff on Runway 2 and the winds are reported as 270 at 20. What is the crosswind and is this within the Langley Aero Club’s 20 kt crosswind limits for the BE-55? [ ] 14. What is the Accelerate / Stop distance for the following conditions? Rwy 17-35 Gross Weight 5,100 lb Flaps Up Field Elevation 4,000 ft MSL Temperature 30° C Winds 350 at 10 kt A. 3960 feet B. 4200 feet C. 4400 feet D. 4280 feet [ ] 15. What is the Single Engine Climb Rate using the conditions in Question 14? A. 80 fpm B. 110 fpm C. 160 fpm D. 180 fpm [ ] 16. Using the data below calculate the Center of Gravity location for N43657. (Copies of the weight and balance data for all Aero Club aircraft are contained in a binder in the Flight Planning room) Pilot and front passenger 380 lb Rear seat passengers 380 lb Baggage 125 lb Full fuel A. 43.22 in aft of datum B. 50.16 in aft of datum C. 84.03 in aft of datum D. 840.3 in aft of datum [ ] 17. What is the True Airspeed for the following conditions (two engines)? Gross Weight 4,800 lb Field Elevation 2,000 ft MSL Temperature at the departure 16° C Cruise Altitude 10,000 ft MSL Cruise Power 60% BHP A. 168 knots B. 181 knots C. 178 knots D. 188 knots [ ] 18. What is the Cruise Fuel Pressure for the conditions in Question 17? A. 5.6 PSI B. 6.5 PSI C. 6.3 psi D. 7.3 psi [ ] 19. What is the Fuel Flow Per Engine (gal / hr) for the conditions in Question 17? A. 9.8 B. 11.0 C. 58.0 D. 75.0