Airplane Flight Manual for Piper PA-34 Seneca
Piper PA-34 Seneca · Flight Manual
Overview
This Airplane Flight Manual (AFM) is specifically designed for the Piper PA-34 Seneca, a twin-engine aircraft known for its reliability and performance. The manual provides essential information for pilots, including operational procedures, performance data, and safety guidelines. It serves as a comprehensive reference for both flight operations and maintenance, ensuring that pilots have the necessary knowledge to operate the aircraft safely and efficiently. The manual is structured to facilitate quick access to critical information, making it an invaluable resource for both experienced and novice pilots.
- Wingspan: 38 ft 10 in; Length: 28 ft 9 in; Max Takeoff Weight: 3,800 lbs.
- Max Cruise Speed: 180 knots; Stall Speed: 61 knots; Service Ceiling: 15,000 ft.
- Conduct thorough preflight inspections and adhere to checklists for all operations.
- In case of engine failure, follow emergency procedures to maintain control and execute a descent.
- Ensure proper weight and balance calculations before flight to maintain safety.
Document
Source
Originally published by www.lakeelmoaero.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Flight Manual
- Pages
- 217
- File size
- 10 MB
- Publisher
- www.lakeelmoaero.com
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 200
- Height (ft)
- 9.9
- Length (ft)
- 28.5
- Propeller
- 76
- Wingspan (ft)
- 38.88
- Engine model
- LIO-360-C1E6
- Max speed (kt)
- 170
- Cruise speed (kt)
- 162
- Empty weight (lb)
- 2,625
- Fuel capacity (gal)
- 100
- Rate of climb (fpm)
- 1,360
- Service ceiling (ft)
- 18,800
- Max takeoff weight (lb)
- 4,200
Performance
- Fuel burn (gph)
- 20.6
- Landing over 50ft
- 1,335
- Takeoff over 50ft
- 1,235
- Landing distance (ft)
- 705
- Takeoff distance (ft)
- 800
- Stall speed clean (kt)
- 58
- Stall speed landing (kt)
- 60
V-speeds
- VS1
- 58
- VSO
- 60
Weight & balance
- Useful load (lb)
- 1,575
- Baggage allowance (lb)
- 100
- Basic empty weight (lb)
- 2,625
- Max landing weight (lb)
- 4,000
- Max takeoff weight (lb)
- 4,200
Common. Rarer than 10% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Piper PA-34 Seneca.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the PA-34 to your watchlist and track it in one place.
More Piper PA-34 Senecamanuals & documents
If you fly the Piper PA-34 Seneca, you may also be researching these.
In this document
Aircraft Specifications
The Piper PA-34 Seneca features a wingspan of 38 feet 10 inches and a length of 28 feet 9 inches. The maximum takeoff weight is 3,800 lbs, with a useful load of approximately 1,200 lbs. The aircraft is powered by two Lycoming IO-360 engines, each producing 180 horsepower.
Performance Data
The PA-34 Seneca has a maximum cruise speed of 180 knots and a stall speed of 61 knots. The service ceiling is 15,000 feet, and the range is approximately 800 nautical miles with standard fuel reserves.
Operating Procedures
Pilots must conduct a thorough preflight inspection, including checks of fuel levels, control surfaces, and engine oil. The manual outlines specific procedures for engine start, taxiing, takeoff, and landing, emphasizing the importance of adhering to checklists.
Emergency Procedures
In the event of an engine failure, pilots should follow the emergency checklist, which includes maintaining control of the aircraft, identifying the failed engine, and executing a controlled descent. The manual provides detailed steps for various emergency scenarios.
Weight and Balance
Proper weight and balance calculations are crucial for safe flight operations. The manual includes charts and formulas to assist pilots in determining the aircraft's center of gravity and ensuring it remains within acceptable limits.
Safety notes
- Always perform a preflight inspection to identify any potential issues before flight.
- Adhere to weight and balance limits to avoid performance degradation or control issues.
- In case of an emergency, follow the established procedures to ensure the safety of all onboard.
Full document text
THE DUPLICATE seneca PILOT'S OPERATING MANUAL BY 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. 34-7350124 PILOT'S OPERATING MANUAL, PART NUMBER 761 506 REVISION PIPER AIRCRAFT CORPORATION APPROVAL SIGNATURE AND STAMP REGISTRATION NO. WYSP PR871130 20 Assurance that the 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 regulations, 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 or 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 GENERAL SPECIFICATIONS APPLICABILITY This manual is applicable to Piper Model PA-34-200 aircraft having serial numbers 34-7250001 through 34-7250189 when Piper Kit 760 607 is installed, 34-7250190 through 34-7250214 when Piper Kit 760 611 is installed and 34-7250215 through 34-7350353. Contact Piper Customer Services for specific information on the application of this manual. REVISIONS The information compiled in the Mot'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. L Revisions 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: 1. 2. Revision pages will replace only pages with the same page number. Insert all additional pages in proper numerical order within each section. II. 3. Page numbers followed by a small letter shall be inserted in direct sequence with the same common numbered page. Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the left hand margin of the page, 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 manual prior to revision are given below: 1-1 through 14, 2-1 through 2-22, 3-1 through 3-26, 4-1 through 4-34, 6-1 through 6-14, 7-1, 8-1 through 8-16, 9-1 through 9-11. REVISIONS ISSUED Current Permanent and Temporary Revisions to the PA-34 Pilot's Operating Manual issued March 10, 1972 are as follows: 761 506 (PR720508) Permanent Revision to F/M Dated May 8, 1972 761 506 (PR720707) 761 506 (PR720802) 761 506 (PR720802) Permanent Revision Dated July 7, 1972 " 761 506 (PR720915) 761 506 (PR721116) 761 506 (PR721220) 761 506 (PR721221) 761 506 (PR730525) 761 506 (PR730919) 761 506 (PR731026) 761 506 (PR740426) 761 506 (PR741014) 761 506 (PR750530) 761 506 (PR750819) 761 506 (PR770401) 761 506 (PR790323) 761 506 (PR830614) Permanent Revision to W/B Permanent Revision to F/M General Specifications Permanent Revision to F/M Permanent Revision to F/M & W/B Dated August 2, 1972 Dated August 2, 1972 Dated September 15, 1972 Dated November 16, 1972 Permanent Revision to F/M & P/O/M Dated December 20, 1972 Permanent Revision to W/B Dated December 21, 1972 Dated May 25, 1973 Permanent Revision to F/M & W/B Permanent Revision to F/M, W/B and P/O/M Permanent Revision to P/O/M Permanent Revision to F/M, W/B and P/O/M Permanent Revision to F/M. W/B and P/O/M Permanent Revision to F/M. W/B and P/O/M Dated September 19, 1973 Dated October 26, 1973 Dated April 26, 1974 Dated October 14, 1974 Dated May 30, 1975 Permanent Revision to F/M and P/O/M Dated August 19, 1975 Permanent Revision to F/M and P/O/M Dated April 1, 1977 Permanent Revision to W/B and P/O/M Dated March 23, 1979 Permanent Revision to F/M and P/O/M Dated June 14, 1983 REVISIONS ISSUED (cont) Current Permanent and Temporary Revisions to the PA-34 Pilot's Operating Manual issued March 10, 1972 are as follows (continued): 761 506 (PR871130) Permanent Revision to Dated November 30, 1987 W/B and P/O/M BLANK PAGE TABLE OF CONTENTS GENERAL SPECIFICATIONS DESCRIPTION-AIRPLANE AND SYSTEMS FLIGHT MANUAL FAA APPROVED EMERGENCY PROCEDURE FAA APPROVED WEIGHT AND BALANCE OPERATING INSTRUCTIONS OPERATING TIPS PERFORMANCE CHARTS HANDLING AND SERVICING BLANK PAGE GENERAL SPECIFICATIONS Performance... Altitude Cruising Speeds (mph) Weights Power Plant...... Fuel and Oil. Baggage Area Dimensions..................... Landing Gear................... 1-1 1-1 1-2 1-2 1-2 1-2 1-2
Show full textShow less
1-3 BLANK PAGE 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. Gross Weight (pounds) 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) Best Rate of Climb Speed (mph) (knots) Best Rate of Climb (ft per min) Best Angle of Climb Speed (mph) (knots) Best Single Engine Rate of Climb Speed (mph) (knots) 4200 800 1235 80 105 (91.5) 1360 90 (78) 105 (91.5) 4000 750 1140 80 105 (91.5) 1460 90 (78) 105 (91.5) Single Engine Rate of Climb @ S.L. (ft per min) Service Ceiling (ft) 230 190 18,800 Absolute Ceiling (ft) 20,000 17,900 19,400 Single Engine Service Ceiling (50 fpm) (left engine out) (ft)** 5200 3650 Single Engine Absolute Ceiling (left engine out) (ft) Top Speed (mph) (knots) 6600 5000 196 (170) 195.3 (169.8) Cruising Speed (75% power at sea level) (mph) (knots) Cruising Speed (75% power at 6000) (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) 173 (150) 171.6 (149.2) 187 (162) 186.3 (162) 185 (160) 183.4 (159.5) 67 (58) 69 (60) 73 (63.5) 76 (66) Landing Roll (flaps down) (ft) (short field) 705*** Landing Over 50 ft Barrier (flaps down) (ft) (short field) 1335*** 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) 20.6 20.6 18.3 18.3 804 804 885 885 *200 BHP, Counter-Rotating Engines, 4200 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. ***This value applies only for the conditions stated on the Landing Distance vs Density Altitude Chart. GENERAL SPECIFICATIONS REVISED: May 30, 1975 1-1 SENECA 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) 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 (lbs per hp) Propeller Diameter (in.) 1-2 4200 4000 2625* 1575* LIO-360-C1E6 IO-360-C1E6 200 2700 5.125 4.375 361.0 8.7:1 350.0 98 5 100/130 8 100 100 15.3 20 24 x 21 38.88 208.7 28.5 9.9 20.1 10.5 76 GENERAL SPECIFICATIONS REVISED: May 30, 1975 LANDING GEAR Wheel Base (ft) Wheel Tread (ft) Tire Pressure (psi) Nose Main Tire Size SENECA 7.0 11.1 31 50 Nose (six-ply rating) 6.00 x 6 Main (eight-ply rating) 6.00 x 6 GENERAL SPECIFICATIONS ISSUED: March 10, 1972 1-3 SENECA 14 -11" 17" 12" 11 2.1"- 11 .17 -21° 7.47"- CENTER LINE MAIN SPAR STA. 186.620 STATIC GROUND LIKE 64 DIAMETER 7" ONEGRAL GENERAL SPECIFICATIONS ISSUED: March 10, 1972