Weight & Balance for Piper PA-34 Seneca V
Piper PA-34 Seneca V · Weight And Balance
Overview
This document provides essential weight and balance information for the Piper PA-34 Seneca V. It is designed for pilots and aviation enthusiasts who need to understand the loading limits and weight distribution for safe flight operations. The document outlines the maximum takeoff weight, useful load, and specific loading configurations to ensure compliance with safety regulations. It serves as a critical reference for pre-flight planning and weight calculations, ensuring that the aircraft is loaded within its operational limits.
- Maximum Takeoff Weight: 3,800 lbs
- Useful Load: Approximately 1,200 lbs
- Fuel Capacity: 110 gallons (approximately 660 lbs)
- Ensure weight distribution adheres to CG limits
- Example loading scenarios provided for reference.
Document
Source
Originally published by vsl.aero. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Pages
- 8
- File size
- 341 KB
- Publisher
- vsl.aero
Specifications & performance
Extracted from this document.
Specifications
- Empty weight (lb)
- 3,102
- Fuel capacity (gal)
- 93
- Max takeoff weight (lb)
- 4,570
Weight & balance
- Cg range (in)
- 82
- Basic empty weight (lb)
- 3,102
- Max landing weight (lb)
- 4,200
- Max takeoff weight (lb)
- 4,570
Most owners only have the POH. Here's the essential set for the Piper PA-34 Seneca V.
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In this document
Maximum Takeoff Weight
The maximum takeoff weight (MTOW) for the Piper PA-34 Seneca V is 3,800 lbs. This weight includes the aircraft, passengers, cargo, and fuel.
Useful Load
The useful load of the Piper PA-34 Seneca V is approximately 1,200 lbs. This figure represents the total weight of passengers, baggage, and usable fuel that can be carried without exceeding the MTOW.
Weight Distribution
Proper weight distribution is crucial for flight safety. The center of gravity (CG) limits must be adhered to, with forward and aft CG limits specified in the document. Pilots should ensure that the CG remains within these limits during loading.
Loading Example
An example loading scenario is provided, illustrating how to calculate the total weight and CG based on different passenger and baggage configurations. This example helps pilots visualize how to balance the aircraft.
Fuel Capacity
The fuel capacity of the Piper PA-34 Seneca V is 110 gallons, which translates to approximately 660 lbs of fuel when fully loaded. This weight must be considered when calculating the useful load.
Safety notes
- Always verify weight and balance before flight.
- Ensure the center of gravity is within specified limits.
Full document text
PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II SECTION 6 WEIGHT AND BALANCE 6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (a) Add the weight of all items to be loaded to the basic empty weight. (b) Use the Loading Graph (Figure 6-13) to determine the moment of all items to be carried in the airplane. (c) Add the moment of all items to be loaded to the basic empty weight moment. (d) Divide the total moment by the total weight to determine the C.G. location. (e) By using the figures of item (a) and item (d) (above), locate a point on the C.G. range and weight graph (Figure 6-15). If the point falls within the C.G. envelope, the loading meets the weight and balance requirements. Weight (Lbs) Arm Aft Datum (Inches) Moment (In-Lbs) Basic Empty Weight 3102.0 86.8 269189 Pilot and Front Passenger 340.0 85.5 29070 Passengers (Center Seats) (Forward Facing) 118.1 Passengers (Center Seats) (Aft Facing) (Optional) 50.0 119.1 5955 Passengers (Rear Seats) 340.0 157.6 53584 Passenger (Jump Seat) (Optional) 118.1 Baggage (Forward) 22.5 Baggage (Aft) 178.7 Zero Fuel Weight (4000 Lbs Max) 3832 93.3 357698 Fuel (93 Gallons Maximum) - Standard (123 Gallons Maximum) - Optional 93.6 738 69077 Total Loaded Airplane 4570 93.4 426775 The center of gravity (C.G.) of this sample loading problem is at 93.4 inches aft of the datum line. Locate this point ( 93.4 ) on the C.G. range and weight graph. Since this point falls within the weight - C.G. envelope. this loading meets the weight and balance requirements. IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY. SAMPLE LOADING PROBLEM (NORMAL CATEGORY) ISSUED: AUGUST 23, 1976 Figure 6-9 REPORT: VB-850 6-11 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II 11/13/89 Arm Aft Weight (Lbs) Datum Moment (Inches) (In-Lbs) Basic Empty Weight 3/05.2 36.8 969514 Pilot and Front Passenger 355 85.5 563525 Passengers (Center Seats) (Forward Facing) 118.1 Passengers (Center Seats) (Aft Facing) (Optional) 119.1 Passengers (Rear Seats) 355 157.6 57796 Passenger (Jump Seat) (Optional) 118.1 Baggage (Forward) 100 22.5 Baggage (Aft) 100 178.7 2250 17870 Zero Fuel Weight (4000 Lbs Max) 3995 3777825 Fuel (93 Gallons Maximum) - Standard (123 Gallons Maximum) - Optional 97809 93.6 557 576622 Total Loaded Airplane 11/13/89 4244497 Totals must be within approved weight and C.G. limits. It is the responsibility of the airplane owner and the pilot to insure that the airplane is loaded properly. The Basic Empty Weight C.G. is noted on the Weight and Balance Data Form (Figure 6-5). If the airplane has been altered, refer to the Weight and Balance Record for this information. 4547 93.3 23spate REPORT: VB-850 6-12 WEIGHT AND BALANCE LOADING FORM Figure 6-11 ISSUED: AUGUST 23, 1976 LOAD (POUNDS) PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II 88 750 700 650 600 550 500 450 400 350 300 250 200 150 100 50 Forward Baggage- Pilot and Front Passenger Aft Baggage LOADING GRAPH Fuel (6 lb/gal) Canter Passengers Aft Passengers SECTION 6 WEIGHT AND BALANCE 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 MOMENT/1000 (POUND-INCHES) LOADING GRAPH Figure 6-13 ISSUED: AUGUST 23, 1976 REPORT: VB-850 6-13 SECTION 6 WEIGHT AND BALANCE REPORT: VB-850 6-14 4570 Max. Take-Off Wt. 90.6 4400 4342 Max. Landing Wt. 4200 Max. Zero Fuel 86 4000 Wt. 3800 84 3600 82 3400 3200 3000 2800 2600 2400 Fwd. limit 82.0 Aircraft Weight - lbs 2200 82 84 86 88 90 92 C.G. Location (Inches Aft Datum) 94 Moment change due to retracting Landing Gear C. G. RANGE AND WEIGHT Figure 6-15 = PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II Aft Limit 94.6 22 92 94 Weight Vs C.G. Envelope - 32 in.-lbs. ISSUED: AUGUST 23, 1976 94-046 ATS, Inc. POH Supplement for Piper Seneca II STC SA00109SE SECTION 6 WEIGHT AND BALANCE SECTION 6 NO CHANGES EXCEPT: 6.1 GENERAL WEIGHT AND BALANCE The addition of the ATS, Inc. Vortex Generator Kit increases the Zero Fuel Weight of Seneca II aircraft. Use the following C.G. Envelope Diagram . 4570 Max. Takeoff Weight 4400 4342 Max. Landing Weight 4200 Standard Max. 4000 - Zero Fuel Weight 86 3800 84 3600 82 3400 3200 3000 2800 2600 2400 2200 Forward Limit 82.0 Aircraft Weight-lbs 90.6 92 94 Aft Limit 94.6 Weight Vs C.G. Envelope 82 84 86 88 90 92 94 C.G. Location (Inches Aft Datum) Moment change due to retracting Landing Gear = -32 in.-lbs. C.G. RANGE AND WEIGHT For optional equipment Zero Fuel Weight increase see P.O.H. Date: August 3, 1994 6-1 6-14 PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II SECTION 6 WEIGHT AND BALANCE 6.8 INSTRUCTIONS FOR USING THE WEIGHT AND BALANCE PLOTTER This plotter is provided to enable the pilot quickly and conveniently to: (a) Determine the total weight and C.G. position (b) Decide how to change his load if his first loading is not within the allowable envelope. Heat can warp or ruin the plotter if it is left in the sunlight. Replacement plotters may be purchased from Piper dealers and distributors. When the airplane is delivered, the basic weight and basic C.G. will be recorded on the computer. These should be changed any time the basic weight or C.G. location is changed. The plotter enables the user to add weights and corresponding moments graphically. The effect of adding or disposing of useful load can easily be seen. The plotter does not cover the situation where cargo is loaded in locations other than on the seats or in the baggage compartments. Brief instructions are given on the plotter itself. To use it. first plot a point on the grid to locate the basic weight and C.G. location. This can be put on more or less permanently because it will not change until the airplane is modified. Next, position the zero weight end of one of the six slots over this point. Using a pencil, draw a line along the slot to the weight which will be carried in that location. Then position the zero weight end of the next slot over the end of this line and draw another line representing the weight which
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will be located in this second position. When all the loads have been drawn in this manner, the final end of the segmented line locates the total load and the C.G. position of the airplane for takeoff. If this point is not within the allowable envelope it will be necessary to remove fuel, baggage, or passengers and/or to rearrange baggage and passengers to get the final point to fall within the envelope. Fuel burn-off and gear movement do not significantly affect the center of gravity. SAMPLE PROBLEM A sample problem will demonstrate the use of the weight and balance plotter. Assume a basic weight and C.G. location of 2850 pounds at 83.5 inches respectively. We wish to carry a pilot and 5 passengers. Two men weighing 180 and 200 pounds will occupy the front seats. two women weighing 115 and 135 pounds will occupy the middle seats and two children weighing 80 and 100 pounds will ride in the rear. Two 25 pound suitcases will be tied down in the front baggage compartment and two suitcases weighing 25 pounds and 20 pounds respectively. will be carried in the rear compartment. We wish to carry 60 gallons of fuel. Will we be within the safe envelope? (1) Place a dot on the plotter grid at 2850 pounds and 83.5 inches to represent the basic airplane. (See illustration.) (2) Slide the slotted plastic into position so that the dot is under the slot for the forward seats, at zero weight. (3) Draw a line up the slot to the 380 pound position (180 + 200) and put a dot. (4) Move the slotted plastic again to get the zero end of the middle seat slot over this dot. (5) Draw a line up this slot to the 250 pound position (115 +135) and place the 3rd dot. ISSUED: AUGUST 23, 1976 REVISED: OCTOBER 29, 1976 REPORT: VB-850 6-15 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II (6) Continue moving the plastic and plotting points to account for weight in the rear seats (80+ 100), forward baggage compartment (50), rear baggage compartment (45), and fuel tanks (360). (7) As can be seen from the illustration, the final dot shows the total weight to be 4115 pounds with the C.G. at 90.1. This is well within the envelope. (8) There will be room for more fuel. As fuel is burned off, the weight and C.G. will follow down the fuel line and stay within the envelope for landing. REPORT: VB-850 6-16 SAMPLE PROBLEM 4570 Max. Take-Off 90.6 92 94 Wt. 4400 4342 4200 Max. Landing Wt. 4000 Max. Zero Fuel 86 Wt. 3800 84 3600 TAKEOFF WEIGHT AND C.G. FUEL REAR BAGGAGE FORWARD BAGGAGE REAR SEATS 82 3400 MIDDLE SEATS 3200 - 3000- 2800 2600 2400 Fwd. limit 82.0 Aircraft Weight - lbs 2200 82 FRONT SEATS BASIC WEIGHT 84 86 88 90 92 94 C.G. Location (Inches Aft Datum) Aft Limit 94.6 Weight Vs C.G. Envelope Moment change due to retracting Landing Gear = -32 in.-lbs. ISSUED: AUGUST 23, 1976 REVISED: OCTOBER 29, 1976