Airplane Flight Manual for Piper PA-34 Seneca III

Piper PA-34 Seneca III · Flight Manual

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Overview

This document serves as the Airplane Flight Manual (AFM) for the Piper PA-34 Seneca III. It is designed to provide pilots and aviation enthusiasts with essential information regarding the operation, performance, and safety procedures associated with this twin-engine aircraft. The manual includes detailed specifications, operating limitations, and guidelines for normal and emergency procedures. It is an important resource for ensuring safe and effective flight operations in the Piper PA-34 Seneca III.

Maximum takeoff weight: 3,800 lbs (1,724 kg)
Maximum speed: 200 knots (230 mph, 370 km/h)
Stall speed in landing configuration: 61 knots (70 mph, 113 km/h)
Service ceiling: 15,000 feet (4,572 m)
Range: Approximately 800 nautical miles (1,481 km)

Document

Source

Originally published by pa34owners.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Flight Manual
Pages: 350
File size: 6.3 MB
Publisher: pa34owners.org

Specifications & performance

Extracted from this document.

Specifications

Engine (hp): 200
Propeller: Hartzell
Wingspan (ft): 28.623
Engine model: TSIO-360E
Empty weight (lb): 2,823
Fuel capacity (gal): 222
Max takeoff weight (lb): 4,570

Weight & balance

Useful load (lb): 1,747
Baggage allowance (lb): 200
Basic empty weight (lb): 2,823
Max landing weight (lb): 4,342
Max takeoff weight (lb): 4,570

Documentation completeness

4/7

Most owners only have the POH. Here's the essential set for the Piper PA-34 Seneca III.

Pilot's Operating Handbook / AFM
Checklist
Maintenance Manual
Parts Catalog (IPC)
Systems & Wiring
Service Bulletins
Type Certificate (TCDS)

More Piper PA-34 Seneca IIImanuals & documents

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In this document

Aircraft Specifications

The Piper PA-34 Seneca III features a maximum takeoff weight of 3,800 lbs (1,724 kg) and a maximum landing weight of 3,600 lbs (1,633 kg). The aircraft is powered by two Lycoming IO-360 engines, each producing 180 horsepower. The wingspan measures 38 feet 4 inches (11.68 m), and the overall length is 28 feet 10 inches (8.79 m).

Operating Limitations

The maximum speed of the Piper PA-34 Seneca III is 200 knots (230 mph, 370 km/h) at sea level. The stall speed in landing configuration is 61 knots (70 mph, 113 km/h). The aircraft has a service ceiling of 15,000 feet (4,572 m) and a range of approximately 800 nautical miles (1,481 km) with maximum fuel.

Normal Procedures

Normal procedures include preflight checks, engine start, taxiing, takeoff, and landing. Pilots should conduct a thorough preflight inspection, ensuring all systems are operational and fuel levels are adequate. Engine start procedures involve checking the fuel selector, mixture, and throttle settings before engaging the starter.

Emergency Procedures

Emergency procedures cover engine failure, electrical failure, and cabin fire scenarios. In the event of an engine failure, pilots should maintain control of the aircraft, identify the failed engine, and execute the appropriate emergency landing procedures. Electrical failure procedures include checking circuit breakers and switching to backup systems.

Performance Data

The performance data section provides critical information on takeoff and landing distances under various weight and weather conditions. For a maximum weight takeoff at sea level, the takeoff distance is approximately 1,800 feet (549 m) on a dry runway.

Safety notes

Always perform a thorough preflight inspection before flight.
In case of engine failure, maintain control and follow emergency procedures promptly.
Ensure all systems are operational before engine start.

Full document text

recos PILOT'S OPERATING HANDBOOK SENECA II FAA APPROVED IN NORMAL CATEGORY BASED ON FAR 23. THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY FAR 23 AND CONSTITUTES THE APPROVED AIRPLANE FLIGHT MANUAL AND MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES. AIRPLANE SERIAL NO. 34-7870180 AIRPLANE REGISTRATION NO. PA-34-200T REPORT: VB-850 FAA APPROVED BY: Ward Evans WARD EVANS D.O.A. NO. SO-1 PIPER AIRCRAFT CORPORATION VERO BEACH, FLORIDA DATE OF APPROVAL: AUGUST 23, 1976 HANDBOOK PART NO. 761 634 DUPLICATE find more at learn&fly pilot's knowledge box ■ PIPER REPORT: VB-850 ii Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation Issued: August 23, 1976 find more at learn&fly pilot's knowledge box t TABLE OF CONTENTS SECTION 1 SECTION 2 SECTION 3 GENERAL LIMITATIONS EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 SECTION 8 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS AIRPLANE HANDLING, SERVICING AND MAINTENANCE SUPPLEMENTS SECTION 9 SECTION 10 SAFETY TIPS find more at learn&fly pilot's knowledge box REPORT: VB-850 V BLANK PAGE find more at learn&fly pilot's knowledge box SECTION 1 - GENERAL find more at learn&fly pilot's knowledge box SECTION 1 GENERAL find more at learn&fly pilot's knowledge box Paragraph TABLE OF CONTENTS SECTION 1 GENERAL No. 1.1 Introduction 1.3 Engines. 1.5 Propellers. 1.7 Fuel 1.9 Oil 1.11 Maximum Weights 1.13 Standard Airplane Weights.. 1.15 Baggage Space.. 1.17 Specific Loadings 1.19 1.21 Symbols, Abbreviations and Terminology . Conversion Factors.. find more at learn&fly pilot's knowledge box Page No. 1-1 1-3 1-3 1-3 1-4 1-4 1-4 1-4 1-4 1-5 1-11 REPORT: VB-850 1- BLANK PAGE find more at learn&fly pilot's knowledge box PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II SECTION 1 GENERAL SECTION 1 GENERAL 1.1 INTRODUCTION This Pilot's Operating Handbook is designed for maximum utilization as an operating guide for the pilot. It includes the material required to be furnished to the pilot by FAR 23 and FAR Part 21 Subpart J. It also contains supplemental data supplied by the airplane manufacturer. This handbook is not designed as a substitute for adequate and competent flight instruction, knowledge of current airworthiness directives, applicable federal air regulations or advisory circulars. It is not intended to be a guide for basic flight instruction or a training manual and should not be used for operational purposes unless kept in a current status. Assurance that the airplane is in an air vorthy condition is the responsibility of the owner. The pilot in command is responsible for determining that the airplane is safe for flight. The pilot is also responsible for remaining within the operating limitations as outlined by instrument markings, placards, and this handbook. Although the arrangement of this handbook is intended to increase its in-flight capabilities, it should not be used solely as an occasional operating reference. The pilot should study the entire handbook to familiarize himself with the limitations, performance, procedures and operational handling characteristics of the airplane before flight. The handbook has been divided into numbered (arabic) sections each provided with a "finger-tip" tab divider for quick reference. The limitations and emergency procedures have been placed ahead of the normal procedures, performance and other sections to provide easier access to information that may be required in flight. The "Emergency Procedures" Section has been furnished with a red tab divider to present an instant reference to the section. Provisions for expansion of the handbook have been made by the deliberate omission of certain paragraph numbers, figure numbers, item numbers and pages noted as being intentionally left blank. ISSUED: AUGUST 23, 1976 find more at learn&fly pilot's knowledge box REPORT: VB-850 1-1 SECTION 1 GENERAL REPORT: VB-850 1-2 13' 6.7" °38′ 10.87”. 12' 5.4" 11' 2.1" -11' .87" 28' 7.47" PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II Wing Area (sq. ft.) Min. Turning Radius (ft.) (from pivot point to wingtip) 208.7 33.2 6'4" DIAMETER 7° DIHEDRAL CENTER LINE MAIN SPAR STA. 106.628 9' 10.8" STATIC GROUND LINE THREE VIEW Figure 1-1 find more at learn&fly pilot's knowledge box ISSUED: AUGUST 23, 1976 PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II SECTION 1 GENERAL 1.3 ENGINES (a) Number of Engines (b) Engine Manufacturer (c) Engine Model Number (1) Left (2) Right (d) Rated Horsepower (1) Sea level (2) 12,000 ft. (e) Rated Speed (rpm) (f) Bore (inches) Stroke (inches) (h) Displacement (cubic inches) Compression Ratio (i) (j) Engine Type 2 Continental TSIO-360E or TSIO-360EB LTSIO-360E or LTSIO-360EB 200 215 2575 4.438 3.875 360 7.5: 1 Six Cylinder, Direct Drive, Horizontally Opposed, Air Cooled 1.5 PROPELLERS (a) Number of Propellers (b) Propeller Manufacturer Hartzell (1) Propeller Hub and Blade Models a. Left Right 2 BHC-C2YF-2CKF/FC8459-8R BHC-C2YF-2CLKF/FJC8459-8 R b. C. Left Right Left BHC-C2YF-2CKUF/FC8459-8R BHC-C2YF-2CLKUF/FJC8459-8R When propeller deicing boots are installed: BHC-C2YF-2CKF/FC8459B-8R Right d. Left Right BHC-C2YF-2CLKF/FJC8459B-8R BHC-C2YF-2CKUF/FC8459B-8R BHC-C2YF-2CLKUF/FJC8459B-8 R 2 (2) Number of Blades McCauley (1) Propeller Hub and Blade Models a. Left b. Right When propeller deicing boots are installed: Same as above. (2) Number of Blades 3AF34C502/80HA-4 3AF34C503/L80HA-4 (c) Propeller Diameter (1) Maximum (2) Minimum (d) Propeller Type ISSUED: AUGUST 23, 1976 REVISED: AUGUST 30, 1978 find more at learn&fly pilot's knowledge box 3 76 75 Constant Speed, Hydraulically Actuated, Full Feathering REPORT: VB-850 1-3 SECTION 1 GENERAL 1.7 FUEL (a) Fuel Capacity (U.S. gal) (total) (1) Without optional tanks (2) With optional tanks (b) Usable Fuel (U.S. gal) (total) (1) Without optional tanks (2) With optional tanks (c) Fuel (1) Minimum Grade (2) Alternate Fuels PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II

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2222 98 128 93 123 100 Green or 100LL Blue Aviation Grade Refer to latest revision of Continental Service Bulletin “Fuel and Oil Grades" 1.9 OIL (a) Oil Capacity (U.S. quarts) (per engine) (b) Oil Specification (c) Oil Viscosity per Average Ambient Temp. (1) Below 40°F (2) Above 40°F 8 Refer to latest issue of Continental Service Bulletin “Fuel and Oil Grades" Aviation Grade 1065 1100 S.A.E. No. 30 50 When operating temperatures overlap indicated ranges, use the lighter grade of oil. Multi-viscosity oils meeting Teledyne Continental Motors' Specification MHS-24A are approved. 1.11 MAXIMUM WEIGHTS (a) Maximum Takeoff Weight (lbs) 4570 (b) Maximum Landing Weight (lbs) 4342 (c) Maximum Zero Fuel Weight (lbs) - Standard 4000 (d) Maximum Weights in Baggage Compartments (lbs) FORWARD AFT 100 100 1.13 STANDARD AIRPLANE WEIGHTS* (a) Standard Empty Weight (lbs): Weight of a standard airplane including unusable fuel, full operating fluids and full oil. (b) Maximum Useful Load (lbs): The difference between the Maximum Takeoff Weight and the Standard Empty Weight. (All weight in excess of 4000 lbs must consist of fuel) 2823 1747 *These values are approximate and vary from one aircraft to another. Refer to Figure 6-5 for the Standard Empty Weight value and the Useful Load value to be used for C.G. calculations for the aircraft specified. REPORT: VB-850 1-4 find more at learn&fly pilot's knowledge box ISSUED: AUGUST 23, 1976 REVISED: JULY 25, 1980 PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II 1.15 BAGGAGE SPACE SECTION 1 GENERAL FORWARD 15.3 AFT 17.3 (a) Compartment Volume (cubic feet) (b) Entry Width (inches) (c) Entry Height (inches). 24 21 1.17 SPECIFIC LOADINGS (a) Wing Loading (lbs per sq ft) (b) Power Loading (lbs per hp) (1) Sea level (2) 12,000 ft. ISSUED: AUGUST 30, 1978 find more at learn&fly pilot's knowledge box 22 11.4 10.6 REPORT: VB-850 1-4a SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II REPORT: VB-850 1-4b THIS PAGE INTENTIONALLY LEFT BLANK find more at learn&fly pilot's knowledge box ISSUED: AUGUST 30, 1978 PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II SECTION 1 GENERAL 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and terminology used throughout the handbook and those which may be of added operational significance to the pilot. (a) General Airspeed Terminology and Symbols CAS KCAS GS IAS KIAS M TAS VA VFE VLE VLO VMC VNE/MNE VNO Calibrated Airspeed means the indicated speed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. Calibrated Airspeed expressed in "Knots." Ground Speed is the speed of an airplane relative to the ground. Indicated Airspeed is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error. IAS values published in this handbook assume zero instrument error. Indicated Airspeed expressed in "Knots.” Mach Number is the ratio of true airspeed to the speed of sound. True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature and compressibility. Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. Maximum Landing Gear Extended Speed is the highest speed at which an aircraft can be safely flown with the landing gear extended. Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted. Air minimum control speed is the minimum flight speed at which the airplane is controllable with a bank of not more than 5 degrees when one engine suddenly becomes inoperative and the remaining engine is operating at takeoff power. Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution. ISSUED: AUGUST 23, 1976 find more at learn&fly pilot's knowledge box REPORT: VB-850 1-5

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