DONE 3G Airplane Systems - Landing Gear Flashcards
- AIRPLANE ONLY*
2. How is the landing gear extended and retracted?
A hydraulic actuator powered by an electrically-driven hydraulic power pack enables the landing gear extension, retraction, and main gear down lock release operations to occur. A pressure switch starts and stops power pack operation and hydraulic pressure is directed by a landing gear lever.
- AIRPLANE ONLY*
1. Describe the landing gear system on this airplane.
The landing gear consists of a tricycle-type system using two main wheels and a steerable nose wheel. Tubular spring steel main gear struts provide main gear shock absorption, while nose gear shock absorption is provided by a combination air/oil shock strut.
- AIRPLANE ONLY*
3. How is the gear locked in the down position?
Mechanical down locks are incorporated into the nose and main gear assembly.
- AIRPLANE ONLY*
4. How is the gear locked in the up position?
A positive “up” pressure is maintained on the landing gear by the hydraulic power pack. To accomplish this, the power pack automatically maintains an operating pressure of 1,000 PSI to 1,500 PSI in the landing gear system.
- AIRPLANE ONLY*
5. How is accidental gear retraction prevented on the ground?
Inadvertent gear retraction is prevented by a safety (squat) switch on the nose gear. Whenever the nose gear strut is compressed (weight of the airplane on the ground), this switch electrically prevents operation of the landing gear system.
- AIRPLANE ONLY*
6. How is the landing gear position indicated in the cockpit?
Amber (gear up) and green (gear down) position indicator lights are provided in the cockpit. They are located adjacent to the landing gear control lever and indicate that the gear is either up or down and locked. Both indicators incorporate a press-to-test feature and also provide dimming shutters for night operation.
Note: If one of the indicator lights should burn out, the design allows for replacement inflight, with the bulb from the other indicator light.
- AIRPLANE ONLY*
7. What type of landing gear warning system is used?
If the manifold pressure is reduced to less than approximately 12 inches at a low altitude with the master switch on, and the landing gear is not locked down, a switch on the throttle linkage will electrically actuate the gear warning circuit of the dual warning unit. An intermittent tone will be heard on the speaker. Also, if the wing flaps are extended beyond 20° while the landing gear is in the retracted position, an interconnect switch in the wing flap system will cause the horn to sound.
- AIRPLANE ONLY*
8. What is the normal length of time necessary for landing gear retraction or extension?
5 to 7 seconds for either extension or retraction of the landing gear.
- AIRPLANE ONLY*
9. Can the landing gear be retracted with the hand-operated pump?
No, retraction of the landing gear cannot be accomplished with the emergency hand pump.
- AIRPLANE ONLY*
10. Describe the braking system on this aircraft.
Hydraulically-actuated disc-type brakes are used on each main gear wheel. A hydraulic line connects each brake to a master cylinder located on each pilot’s rudder pedals. By applying pressure to the top of either the pilot’s or copilot’s set of rudder pedals, the brakes may be applied.
- AIRPLANE ONLY*
11. How is steering accomplished on the ground? (FAA-H-8083-31)
Light airplanes are generally provided with nosewheel steering capabilities through a simple system of mechanical linkages connected to the rudder pedals. When a rudder pedal is depressed, a spring-loaded bungee (push-pull rod) connected to the pivotal portion of a nosewheel strut will turn the nosewheel.
- AIRPLANE ONLY*
12. What are the landing gear tire pressures?
Nosewheel Tire Pressure— 40–50 PSI; 5.00-5, 6-ply rated tires
Main Wheel Tire Pressure— 60–68 PSI; 15x6.00-6, 6-ply rated tires
