They are air cooled, direct driven and horizontally opposed.Īsymmetric thrust is eliminated by counter-rotation of the engines.Įxhaust: The exhaust system is a crossover type with exhaust gases directed outboard of the nacelle into muffler heater to minimize noise and provide heated air for the cabin.Ĭowl Flaps: Manually operated by control levers.
Each engine is ratedĪt 200 HP at 2700 RPM. The aircraft is powered by two four cylinder, lycoming fuel injected engines. Maximum Crosswind Component for Landing is 15 MPHĪircraft aluminum alloy for structural components of airframe Single Engine Service Ceiling MGW 5,000 ft. Oil Capacity 8 quarts each engine, 6 quarts minimum each sideįuel Capacity 98 gallons total, 93 gallons useable Usable fuel 46.5 gallons in each wing – Total usable, 93 galĮngine types 4 cylinder horizontally opposed fuel injected Locoing IO-360 Unusable fuel 2.5 gallons in each wing - Total Unusable 5gal White Arc (Flaps Extended Range): 69-125MPH Max baggage Capacity 100lbs forward compartment and 100 lbs rear compartment. V Service Ceiling: - The altitude at which a specified kind of aircraft cannot, because of reduced atmosphericpressure, climb faster than a 100 FPM (Feet Per Minute) rate for multi engine and 50 FPM for single engine.Ībsolute Ceiling: - The maximum altitude above sea level at which an aircraft can maintain horizontal flight under standard atmospheric conditions. to exceed 245 degrees F.ĭiameter between 74-76 inches no more or less Should be open for ground operations and in climb. exceedsĬOWL FLAPS: Cowl flaps provided to allow manual control of engine temperatures. OIL COOLER: Oil cooler winterization plate has to be removed when ambient temp. Right engine Lycoming LIO-360-C1E6 fuel injected
Left engine Lycoming IO-360-C1E6 fuel injected. Stabilator Incorporates an anti servo tab, improving longitudinal stability Wing Flaps Slotted/ mechanically operatedįuel Tanks 2 interconnected tanks form integral part of each wing Tire Size: Nose 6ply 600圆 - Mains 8ply 600圆įuselage Conventional Semi Monocoque structure THE FOLLOWING INFORMATION IS PROVIDED FOR TRAINING PURPOSES ONLY - THE OFFICIAL PILOT OPERATING HANDBOOK IS THE FINAL AUTHORITY FOR ALL SENECA I SYSTEMS INFORMATION AND LIMITATIONS. about Piper Seneca and we hope that this information is very valuable for you and thats all your Instructor wants you to know for your Flight Test.įor Flight test Guide, Click the following link below:įor weight and balance software contact us by clicking on this. After Going through Multi Engine POH and different books, we found out this valuable info.
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