MEL PA-44 Seminole

This engine would most adversely affect the performance of the airplane if it were to fail.

minimum controllable airspeed, minimum speed at which the aircraft is directionally controllable

Critical Engine Failed/Windmilling, Operating Engine Takeoff Power, Most Unfavorable Weight, Bank less than 5 degrees, Aft CG, Takeoff Configuration, Sea level conditions, Ground Effect, Gear Up.

Torque, P-Factor, Accelerated Slipstream, Spiraling Slipstream.

Due to the direction of rotation of the props a yawing tendency occurs when the left engine fails, making it the critical engine.

Operating right-hand engine will produce a more severe yaw towards the dead engine due to the direction of rotation of the props. More "bite" from downward blade which is further from the center of the aircraft.

Due to accelerated air over the wing it causes greater lift and a rolling tendency.

Left Engine Critical, The airflow from the left engine is moving around the aircraft and pushing on the rudder causing a yaw to the left. Right engine has no effect.

Light is unfavorable. An increase in weight causes Vmc to decrease because of the greater horizontal component of lift. With a greater horizontal component of lift (max 5 degrees) less rudder is required thus decreasing Vmc.

1 degree of bank changes Vmc 3 knots, bank toward good engine decreases Vmc.

A longer arm means more effective rudder and a lower Vmc, but a shorter arm means rudder is less effective and increases vmc.

As we climb, pressure decreases. Power also decreases with altitude causing less of a yaw and less rudder required. Sea level conditions increases vmc.

Anti-servo tab used for trimming and returning the flight control to a neutral point.

Manual and spring loaded. 0, 10, 25 and 40 degrees

Plain, SLotted, Split, Fowler

Allow aircraft to operate at a higher AoA. Allow aircraft to fly at lower speeds as well as have shorter takeoff and landing distances.

Fixed Slot, Moveable Slot, Leading Edge Flap, Leading Edge Cuff

Reduce lift and increase drag. Often used for roll control and they are deployed at the same time allowing the aircraft to descend without gaining speed.

2 Lycoming O-360 A1H6, 4-cylinder, direct drive, horizontally opposed, 180hp at 2700rpm at sea level standard day. Air and oil cooled.

Hartzell 2-blade, constant speed, conrollable pitch and feathering. Asymmetrical thrust eliminated due to counter-rotating engines.

Prop maintaims the RPM selected by the prop control lever regardless of the pitch or throttle position.

Oil and Nitrogen pressure.

Feathered.

Stores oil pressure, allows prop to unfeather without oil pressure while engine is starting.

Hydraulically operated, fully retractable, tricycle.

downlock hooks engage, springs maintain force until released by hydraulic pressure.

Red GEAR UNSAFE, gear is neither in the full up or full down position.

Gear is not down and, 1. MP is below 14 inches. 2. The gear selector is in the UP position on the ground. 3. Gear selector is UP and flaps are extended to 25 or 40 degrees.

30 degree arc either side of center.

Two single disc, double puck brake assemblies, one on each main gear.

Two 55 gallon tanks, 1 gallon unusable each tank

2 belt driven 14 volt 70amps.

35amp hour, 12volt.

6 buses. Main, Nonessential, Tie, Avionics 1&2, and Battery.

Fed from tie bus. Standby Lights, recog lights, cabin heater, cabin vent, and blower.

Bus 1 has Nav1, Comm1, Transponder, Pitch Trim, compass, and audio select. Bus 2 has comm2, nav2, adf, and marker beacons.

distributes power to the other systems through breakers.

Uses 1/2 gallon and hour from left tank

Requires more taildown force. Requires more lift. Faster TAS required for takeoff and landing, longer takeoff and landing,higher stall speed, slower cruising speed, less controllable but greater positive static stability.

Requires less taildown force, Slower TAS for takeoff and landing, Shorter Landing and takeoff distance, lower stalling speed due to lower AOA, higher cruise speed, Increased endurance and range, Less positive static stability but more controllable.

Airplane,Multi-Engine Land, no type.

greater than 12,500lbs, turbojet, or anything the administrator deems should get a type certificate.

Airplane, Multi-engine land,Instrument.

55

57

56

82

82

75

82

88

88

109

140

140

111

135

169

202

3816lbs

3800lbs

3800lbs