Performance Data for the Piper PA-34 Seneca III

Piper PA-34 Seneca III · Performance Data

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Overview

This document provides performance data specifically for the Piper PA-34 Seneca III. It is intended for pilots and aviation enthusiasts who require detailed information on the aircraft's capabilities, limitations, and operational parameters. The manual includes critical performance metrics such as takeoff and landing distances, climb rates, fuel consumption, and weight limits. Understanding this data is essential for safe and efficient flight operations. The document serves as a reference for flight planning and operational decision-making, ensuring that pilots can maximize the performance of the Seneca III while adhering to safety standards.

Takeoff distance at sea level: approximately 1,500 feet.
Rate of climb: approximately 1,200 feet per minute at sea level.
Landing distance on a dry runway: approximately 1,200 feet.
Maximum takeoff weight: 3,800 pounds.
Cruise fuel consumption: about 12 gallons per hour at 65% power.

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Document details

Type: Performance Data
Pages: 189
File size: 13 MB
Publisher: jasonblair.net

Specifications & performance

Extracted from this document.

Specifications

Engine (hp): 200
Height (ft): 9.9
Length (ft): 28.5
Propeller: LIO-360-C1E6
Wingspan (ft): 38.88
Engine model: IO-360-C1E6
Empty weight (lb): 2,557
Fuel capacity (gal): 100
Rate of climb (fpm): 1,460
Service ceiling (ft): 18,800
Max takeoff weight (lb): 4,000

Performance

Fuel burn (gph): 20.6
Landing over 50ft: 1,335
Takeoff over 50ft: 1,140
Landing distance (ft): 705
Takeoff distance (ft): 750
Stall speed clean (kt): 67
Stall speed landing (kt): 73

V-speeds

VX: 90
VY: 105
VS1: 67
VSO: 73

Weight & balance

Useful load (lb): 1,443
Baggage allowance (lb): 100
Basic empty weight (lb): 2,557
Max landing weight (lb): 4,000
Max takeoff weight (lb): 4,000

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

Takeoff Performance

This section outlines the takeoff distances required under various weight and environmental conditions. For a standard day at sea level, the takeoff distance is approximately 1,500 feet. Factors such as aircraft weight, altitude, and temperature significantly affect this distance.

Climb Performance

The climb performance section details the rate of climb at different weights and configurations. The Piper PA-34 Seneca III can achieve a rate of climb of approximately 1,200 feet per minute at sea level under optimal conditions.

Landing Performance

Landing distances are provided for various weights and configurations. The landing distance on a dry runway is approximately 1,200 feet, which can vary based on wind conditions and aircraft weight.

Weight Limitations

The maximum takeoff weight for the Piper PA-34 Seneca III is 3,800 pounds. Pilots must ensure that the aircraft is within this limit for safe operations.

Fuel Consumption

Fuel consumption rates are detailed for various phases of flight. The aircraft typically consumes about 12 gallons per hour during cruise flight at a power setting of 65%.

Safety notes

Always verify weight and balance before flight.
Monitor fuel levels to avoid running out during flight.

Full document text

TO seneca 13904 PILOT'S OPERATING MANUAL NIST DUPLICATE 'BY ona ☐ PIPER This manual is incomplete without an APPROPRIATE FAA APPROVED AIRPLANE FLIGHT MANUAL and an APPROPRIATE WEIGHT AND BALANCE REPORT. : WARNING EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS MANUAL TO APPLICABLE: AIRCRAFT THIS MANUAL REVISED AS INDICATED BELOW -OR SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION. SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED MODEL PA-34-200.. AIRCRAFT SERIAL NO. 34-7250030 .' REGISTRATION NO.¡ ___!C-GTXR PILOT'S OPERATING MANUAL, PART NUMBER 761 506 REVISION PR§71130 PIPER AIRCRAFT CORPORATION APPROVAL SIGNATURE AND STAMP Stephanie J. Chartaan Stephanie J. Chǎrtier Assurance that t airplane is in an airworthy 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 outlined by the Airplane Flight Manual, instrument markings, and placards. *This Pilot's Operating Manual is not designed as a substitute for adequate and competent flight instruction, knowledge of the current airworthiness directives, applicable federal air egulations, or advisory circulars. It is not intended to be a guide for basic flight instruction or a training manual for transition from single to multi-engine, flying. If an inconsistency of information exists between the Pilot's Operating Manual and the Airplane Flight Manual, approved by the FAA, the Airplane Flight Manual shall be the authority A complete of partial replacement of this manual, Part No. 761 506, may be obtained only from Piper Customer Services, Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation 761 506 Issued: March 1972 Num. TABLE OF CONTENTS GENERAL SPECIFICATIONS DESCRIPTION - AIRPLANE AND SYSTEMS AIRPLANE FLIGHT MANUAL F.A.A. APPROVED EMERGENCY PROCEDURES F.A.A. APPROVED EMERGENCY PROCEDURES: WEIGHT AND BALANCE LOADING INSTRUCTIONS OPERATING INSTRUCTIONS OPERATING TIPS PERFORMANCE CHARTS HANDLING AND SERVICING Y : : C GENERAL SPECIFICATIONS Performance Weights Power Plant Fuel and Oil.. Baggage Area Dimensions Landing Gear 3-View C 1-1 1-2 1-2 1-2 1-3 1-3 1-3 14 : 1-i C C C GENERAL SPECIFICATIONS SENECA PERFORMANCE Published figures are for standard airplanes flown at gross weight" under standard conditions at sea level, unless otherwise stated. Performance for a specific airplane may vary from published figures depending upon the equipment installed, the condition of engine, airplane and equipment, atmospheric conditions and piloting technique. Each performance figure below is subject to the same conditions as on the corresponding performance chart from which it is taken in the Performance Charts Section. Gross Weight (pounds) Takeoff Run, flaps up, sea level (ft) Takeoff Distance Over 50-ft Obstacle, flaps up, sea level Take-off Run (ft) (short field effort, flaps 25°) Take-off Distance Over 50 ft Barrier (ft) (short field effort, flaps 25°) Minimum Controllable Single Engine Speed (mph). Rate of Climb, sea level (ft per min) Rate of Climb, sea level, single engine (ft per min) Best Rate of Climb Speed (mph) Best Rate of Climb Speed, sea level, single-engine (mph) Best Angle of Climb Speed, sea level (mph) Best Angle of Climb Speed, sea level, single engine (mph) Max Speed, sea level Max Speed Optimum Alt, 6000 ft, 75% power (TAS) (mph) Service Ceiling (ft) Service Ceiling, left engine out (ft) Absolute Ceiling (ft) Absolute Ceiling, left engine out (ft) Cruise Speed at best power mixture (mph) 65% power, 9,000 ft 55% power, 13,300 ft Range at best power mixture (mi) 75% power, 6,000 ft 65% power, 9,000 ft 55% power, 13,300 ft Cruise Speed at best economy mixture (mph) 75% power, 6,000 ft 65% power, 9,000 ft 55% power, 13,300 ft :. *200 BHP, Counter-Rotating Engines, 14200 lb. G.W., Maximum Take-off Weight 4000 lb. G.W., Maximum Landing Weight **5000 Ft. Single Engine Service Ceiling Occurs at 4030 Pounds Gross Weight. GENERAL SPECIFICATIONS REVISED: MAY 30, 1975 【4200] 1·000 1420 800 1235 lmc 80- 1360 190 Vy 105 Vyse 105 Vx 90 Vxse 93 195 186 17,900 3650 19,400 5000* ** 183 178 729 797 876 179 174 168 1-I I SENECA PERFORMANCE (cont) Range at best economy mixture (mph) 75% power, 6,000 ft 65% power, 9,000 ft 55% power, 13,300 ft Stalling Speed, gear and flaps down, power off (mph) Vso 804 885 969 69 Stalling Speed, gear down and flaps up, power off (mph) Fuel Consumption, 75% power, both engines (gph) Fuel Consumption, 65% power, both engines (gph) Landing Roll (flaps down) (ft) Vs 76 20.6 18.3 705* 1335* Landing Over 50 ft Barrier (flaps down) (ft) *4000 lb. G.W., Maximum Landing Weight WEIGHTS Gross Weight (lbs) Max. Take-off Max. Landing Empty Weight (Standard) (lbs) USEFUL LOAD (Standard) (lbs) *These weights are approximate POWER PLANT Right Engine - Lycoming Left Engine - Lycoming Rated Horsepower Rated Speed (rpm) Bore (in.) Stroke (in.) Displacement (cubic in.) Compression Ratio Dry Weight (lbs) FUEL AND OIL Fuel Capacity (U.S. gal) Unusable fuel Fuel, Aviation Grade (minimum octane) Oil Capacity (qts) (each engine) 1-2 4200 4000 2656* 1544* LIO-360-C1E6 IO-360-C1E6 200 2700 5.125 4.375 361.0 8.7:1 · 350.0 98 5 100/130 8 GENERAL SPECIFICATIONS REVISED: MAY 30, 1975 i C APPLICABILITY This manual is applicable to Piper Model PA-34-200 aircraft having serial numbers 34-7450001 through 34-7450220. Contact Piper Customer Services for specific information on the application of this manual. REVISIONS The information compiled in the Pilot's Operating Manual will be kept current by revisions distributed to the airplane owners. · Revision material will consist of information necessary to update the text of the present manual and/or to add information to cover added airplane equipment. I. Revisions

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Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the manual in accordance with the instructions given below: Revision pages will replace only pages with the same page number. 1. 2. Insert all additional pages in proper numerical order within each section. 3. Page numbers followed by a small letter shall be inserted in direct sequence with the same common numbered page. II. Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the left hand margin of the pagė, opposite revised, added or deleted material. A line opposite the page number or section title and printing date, will indicate that the text or illustration was unchanged but material was relocated to a different page or that an entire page was added. Black lines will indicate only current revisions with changes and additions to or deletions of existing text and illustrations. Changes in capitalization, spelling, punctuation or the physical location of material on a page will not be identified by symbols. III. Original Pages Issued ' The original pages issued for this mandat prior to revision are given below: 1-1 through 1-4, 2-1 through 2-24, 3-1 through 3-32, 41 through 4-6, 5-1 through 50, 7-1 through 7-14, 8-1 through 8-2, 9-1 through 16, 10-1 through 10-11. PILOT'S OPERATING MANUAL LOG OF REVISIONS Current Revisions to the PA-34-200 Seneca Pilot's Operating Manual, 761 577, issued July 16, 1973. Revision Revised Pages Description Date Rev. 1 - 761 577 AFM Added Rev. 1 to Report VB-563. Aug. 31, 1973 (PR730831). ¨W/B Added Rev. 1 to Report VB-552. Rev. 2-761 577 2-i Added Ice Protection System. March 4, 1974 (PR740304) 2-24 Added Ice Protection System. 2-25, 2-26, Added Pages. 2-27 2-28, 2-29 AFM Added Pages; Relocated material from Page 2-24. Added Rev. 2 to Report VB-563. W/B Added Rev. 2 to Report VB-552. ;" 7-i 7-13 7-14 7-15 Added Operation In Known Icing Conditions. Added Operating Instructions to Known Icing Conditions. Relocated material to Page 7-15. Added Page; Relocated material from Page 7-14. Added PAC Approval Form. Rev. 3-761 577 ii ! June 14, 1974 (PR740614) Added Applicability and Item III. Original Pages Issued. A F/M W/B Rev. 4-761 577 (PR740628) iv 1-2 2-15 " A F/M W/B 7-2 7-3 7-6 9-i 9-7 Added Rev. 3 to Report: VB-563. Added Rev. 3 to Report: VB-552. (NOTE: AIRCRAFT DELIVERED WITH MANUALS PRIOR TO THIS REVISION DO NOT REQUIRE THIS REVISION.) Revised Applicability. Revised Empty Weight and Useful Load: Revised Alternator and Starter Schematic. Added Rev. 4 to Report VB-563) ' Added Rev. 4 to Report VB-552. Added new item 13; relocated info to Page 7-3. Added info from Page 7-2, …….. Revised item 18. Revised Index. Revised Multi-Engine Climb Chart Nomenclature. June 28, 1974 h C C D: PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont) Revision Revised Pages Description Rev. - 4 (cont) 9-8 Revised Single-Engine Climb Chart Nomenclature. 9-9 9-10 Rev. 5 761 577 1-1 Revised Range figures. (PR750530) 1-2 2-1 2-10 2-19 Revised True Airspeed Chart Nomenclature. Revised Range Chart Nomenclature. Revised Range figures; revised fuel capacity. Revised fuel capacity - The Airplane. Revised fuel capacities and usable fuel - Fuel System. Revised fuel capacity on quantity gauges - Instrument Panel. A F/M Added Rev. 5 to Report: VB-563. W/B 9-10 Added Rev. 5 to Report: VB-552. Revised Cruise Performance Chart. 10-7 Rev. 6-761 577 A F/M (PR750818) 7-5 8-1 8-2 Revised fuel capacities - Filling Fuel Tanks. Added Rev. 6 to Report: VB-563. Revised Pretakeoff Check item '2.d. Revised item 10. (Fuel Warning Tip). Added items 13. and 14. Date. May 30, 1975 August 18, 1975 Rev. 7 - 761 577, (PR760709) 2-3 2-4 377 Added info from. page 2-4. Rev 8-761-577 (PR770329) 2-5 2-6 A F/M W/B 8-1 Moved info to page 2-3; added info from page 2-5; revised existing info. Moved info to page 2-4; revised existing info. Added emergency gear knob info. Revised placard in illustration; revised existing info. Added Rev. 7 to Report: VB-563. Added Rev. 6 to Report: VB-552. Revised Operating Tip no. 10; moved item 11 to page 8-2. Added info from page 8-1. Deleted info under Engines, 8-2 9-13 Added note to graphi 9-14 Added note to graph. 2-3 A F/M 7-5 7-15 8-2 Added Rev. 8 to Report: VB-563. Added info to item 3. under Taxi. Revised Note: Added item 15. } July 9, 1976 14 March 29, 1977 : iv-a PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont) Revision Revised Pages Description Rev. 9 - 761 577 (PR790326) 2-1 Revised The Airplane description. 2-2 Revised Airframe description. 2-10 2-12 W/B 7-14 Date March 26, 1979 Rev. 10 761 577 2-1 (PR830606) A F/M W/B Revised Fuel System description. Revised Electrical System description. Added Rev. 7 to Report: VB-552. Revised ELT description. The Airplane - revised text. Added Rev. 9 to Report: VB-563. Added Rev. 8 to Report: VB-552. June 6, 1983 Rev. 11761 577 W/B Added Rev. 9 to Report: VB-552. Nov. 30, 1987 (PR871130) 7-2 Revised Walk-Around Inspection Checklist. iv-b C GENERAL SPECIFICATIONS SENECA PERFORMANCE Published figures are for Standard PA-34* airplanes flown at gross weight under standard condition at sea level unless otherwise stated. Performance for a specific airplane may vary from published figures depending upon the equipment installed, the condition of engines, airplane and equipment, atmospheric conditions and piloting technique. Take-off Run (ft) (short field effort, flaps 25°) C 750 Take-off Distance Over 50 ft Barrier (ft) (short field effort, flaps 25°) Minimum Controllable Single Engine Speed (mph) · Best Rate of Climb Speed (mph) (knots) 1140 80 105 (91.5) Best Rate of Climb (ft per min) 1460 Best Angle of Climb Speed (mph) (knots) 90 (78) Best Single Engine Rate of Climb Speed (mph) (knots) 105 (91.5) Single Engine Rate of Climb @ S.L. (ft per min) 230 Service Ceiling (ft) 18,800 Absolute Ceiling (ft) 20,000 Single Engine Service Ceiling (50 fpm) (ft) 5200 Cruising Speed (75% power at 6000) (mph) (knots) Single Engine Absolute Ceiling (ft) Top Speed (mph) (knots) Cruising Speed (75% power at sea level) (mph) (knots) Optimum Cruising Speed (65% power at 9000) (mph) (knots) Stalling Speed (gear and flaps down) (power off) (mph) (knots) Stalling Speed (gear down and flaps up) (power off) (mph) (knots) Landing Roll (flaps down) (ft) (short field) Landing Over 50 ft Barrier (flaps down) (ft) (short field) Fuel Consumption (75% power) (gph) (both engines) Fuel Consumption (65% power) (gph) (both engines) Cruising Range (75% power at 6000 ft) (mi) Cruising Range (65% power at 9000 ft) (mi) 6600 196 (170) 173 (150) 187 (162) 185 (160) 67. (58) 73 (63.5) ** 705 ** 1335 20,6 18.3 804 $885 *200 BHP, Counter-Rotating Engines, 4000 lb. G.W. **This value applies only for the conditions stated on the Landing Distance vs Density Altitude Chart. GENERAL SPECIFICATIONS REVISED: August 20, 1975 1-1 SENECA WEIGHTS Gross Weight (lbs) Empty Weight (Standard) (lbs) USEFUL LOAD (Standard) (lbs) * These weights are approximate POWER PLANT Right Engine - Lycoming Left Engine - Lycoming Rated Horsepower Rated Speed (rpm) Bore (in.) Stroke (in.) Displacement (cubic in.) Compression Ratio Dry Weight (lbs) . FUEL AND OIL 4000 2557* 1443* LIO-360-C1E6 IO-360-C1E6 200 2700 5.125 4.375 361.0 8.7:1 350.0 Fuel Capacity (U.S. gal) Unusable fuel Fuel, Aviation Grade (minimum octane) Oil Capacity (qts) (each engine) BAGGAGE AREA Maximum Baggage (lbs) Forward Compartment Maximum Baggage (lbs) Rear Compartment Baggage Space (cubic ft) Forward Compartment Baggage Space (cubic ft) Rear Compartment Baggage Door Size (in.) Forward Compartment DIMENSIONS Wing Span (ft) Wing Area (sq ft) Length (ft) Height (ft) Wing Loading (lbs per sq ft) Power Loading (Ibs per hp) Propeller Diameter (in.) 1-2 98 5 100/130 8 100 100 15.3 20 24 x 21 38.88 208.7 28.5 9.9 19.2 10.0 76 GENERAL SPECIFICATIONS REVISED: May 30, 1975 LANDING GEAR Wheel Base (ft) Wheel Tread (ft) Tire Pressure (psi) Nose Tire Size SENECA 7.0 11.1 31 Main Nose (six-ply rating) 50 6.00 x 6 Main (eight-ply rating) 6.00 x 6 GENERAL SPECIFICATIONS ISSUED: April 15, 1971 1-3

All Piper PA-34 Seneca III performance data