Piper Seneca II Pa-34-200t Service Repair Workshop Manual

This is the COMPLETE Service and Repair Manual for the Piper Seneca II Pa-34-200t Service Repair Workshop Manual. It covers every single detail.

PIPER SENECA II SENECA SERVICE MANUAL PA-34-200T INTRODUCTION 1-1. GENERAL. This manual contains service and maintenance instructions for the Piper PA-34-200T Seneca II, designed and manufactured as a versatile airplane in the personal and business aviation field, by the Piper Aircraft Corporation, Vero Beach, Florida. 1-2. SCOPE OF MANUAL. Sections II and III comprise the service part of this manual; whereas, Sections IV through XIV comprise the maintenance instructions. The service instructions include ground handling, servicing and inspection. The maintenance instructions for each system include troubleshooting, removal and installation of components, and corrective maintenance and testing; each major system of the airplane is covered in a separate section. Only qualified personnel should perform the operations described in this manual. The description of the airplane included in this section is limited to general information. Section II gives leading particulars and principal dimensions, along with ground handling, while each major system is described in its appropriate section of the manual For a more detailed description of the airplane, refer to the Owner's Handbook. 1-3. DESCRIPTION. The Seneca II is a six place (seventh seat optional), twin engine, low-wing monoplane of all metal construction. The following paragraphs provide descriptions of the major components and systems. 1-4. WING. The laminar flow wing is of all metal stressed-skin, full cantilever, low-wing design, consisting of two wing panels bolted to a spar box assembly in the fuselage. The wing tips are removable. The ailerons are cable and push rod controlled and are aero dynamically balanced. The trailing edge wing flaps are manually operated. 1-5. EMPENNAGE. The empennage consists of the fin, rudder, rudder trim tab, stabilator and stabilator trim tabs. The rudder and stabilator are statically balanced. 1-6. FUSELAGE. The fuselage consists of three basic units: the nose section, the cabin section and the sheet-metal tail cone.1-7. LANDING GEAR. The tricycle landing gear is of the retractable air-oil strut type, consisting of a nose wheel and two main wheels. 1-8. BRAKE SYSTEM. The standard brake system is operated hydraulically by dual toe brakes located on the rudder pedals or by a hand lever connected to a single brake cylinder below and behind the left center of the instrument panel. 1-9. ENGINES AND PROPELLER. The airplane is powered by two Teledyne Continental six cylinder, direct drive, wet sump, horizontally opposed turbocharged engines. The left engine rotation is in the right-hand direction while the right engine rotates in the left-hand direction. The propellers are Hartzell full feathering, constant speed units controlled by a governor mounted on each engine. 1-10. FUEL SYSTEM. The fuel system consists of two interconnected aluminum fuel tanks in each wing, having a combined capacity of 49 U.S. gallons, for a total capacity of 98 U.S. gallons. With optional fuel

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