Weight and Balance for the Piper PA-34 Seneca V

Piper PA-34 Seneca V · Weight And Balance

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Overview

This document provides essential weight and balance information for the Piper PA-34 Seneca V, specifically the aircraft with registration N8502V. It outlines the loading weights, arm measurements, and moments necessary for determining the aircraft's center of gravity (C.G.) and overall weight. The document emphasizes the pilot's responsibility to ensure the aircraft is loaded within the approved weight and C.G. envelope to maintain performance and safety during flight. It includes tables and graphs to assist in calculating the loading configuration and highlights the importance of proper loading to avoid performance issues and safety hazards.

Licensed Basic Weight: 2807.62 lbs
Arm Measurement: 85.49 inches
Total Fuel Capacity: 93 gallons (6 lbs/gallon)
Pilot must ensure proper loading to avoid performance issues
C.G. position is critical for safe flight characteristics

Document

Source

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

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Document details

Type: Weight And Balance
Pages: 4
File size: 312 KB
Publisher: angelaviation.com

Specifications & performance

Extracted from this document.

Specifications

Fuel capacity (gal): 93

Weight & balance

Basic empty weight (lb): 2,807.62

Documentation completeness

6/7

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In this document

Loading Weight Table

The loading weight table lists various components affecting the total weight of the Piper PA-34 Seneca V. It includes the licensed basic weight of 2807.62 lbs, the arm measurement of 85.49 inches, and the moment of 240030.56 lbs-inch/1000. Additional entries for pilot and passenger weights, fuel capacity (93 gallons), and baggage allowances are also included.

Pilot Responsibility

The document stresses that it is the pilot's responsibility to ensure the aircraft is loaded correctly. Misloading can lead to performance issues, such as reduced single-engine performance and potential safety hazards like stalls or spins if the C.G. is improperly positioned.

Center of Gravity Considerations

The center of gravity is crucial for the aircraft's flight characteristics. An aft C.G. can lead to premature rotation on take-off and reduced longitudinal stability, increasing the risk of stalls. The document provides guidance on how to calculate and verify the C.G. position to ensure safe operation.

Weight vs. Center of Gravity Envelope

Graphs included in the document illustrate the allowable weight versus center of gravity envelope for the Piper PA-34 Seneca V. Pilots must ensure that the aircraft remains within this envelope during flight to maintain safety and performance.

Safety notes

Misloading can lead to reduced performance and safety hazards.
An aft C.G. can increase the risk of stalls and spins.

Full document text

Weight and Balance Table N8502V Seneca PA-34-200 LOADING WEIGHT lbs Arm Aft Datum Inches MOMENT lbs-inch/1000 1 Licensed Basic Weight 2807.62 85.49 240030.56 2 Pilot and Front Passenger 3 Passengers (Center Seats) 4 Passengers (Rear Seats) 5 Passenger (Jump Seat) 6 Useable Fuel (6lbs/Gallon) Standard Tanks 93 Gal. Maximum 7 Baggage (Forward) 8 Baggage (Aft) 10 Total Loaded Airplane *It is the responsibility of the pilot to ensure that the airplane is loaded properly. In order to achieve the performance, safety and good flying characteristics which are designed into the aircraft, the Seneca must be flown with the weight and center of gravity (C.G./CofG) position within the approved envelope. The aircraft offers a tremendous flexibility of loading. You can carry a large payload (distributed in a variety of combinations of passengers and cargo) or a large amount of fuel. However, you cannot fill the aircraft with seven adults and full fuel tanks. With the flexibility comes responsibility. The pilot must ensure that the airplane is loaded within the loading envelope before the pilot makes a take-off. Misloading carries consequences for any aircraft. An overloaded airplane will take off, climb or cruise and well as when it is properly loaded. The heaver the airplane is loaded the less single-engine performance it will have, and the pilot may be deprived of one of the safety advantages of twin-engine flight. Center of gravity is determining factor in flight characteristics. If the C.G. is too far aft, the airplane may rotate prematurely on take-off or try to pitch up during climb. Longitudinal stability will be reduced. This can lead to inadvertent stalls and even spins; and spin recovery becomes more difficult as the center of gravity moves aft of the approved limit. A properly loaded aircraft, however, will perform as intended. The Seneca is designed to provide excellent performance and safety within the flight envelope. Using the basic weight and C.G. location, the pilot can easily determine the weight and C.G. position for the loaded airplane by means of a plotter which is furnished with the aircraft or compute the total weight and moment and then determine whether they are within the approved envelope. IT IS THE RESPONSIBILITY OF THE PILOT TO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY. _________________________ _________________________ ________________________ Student Name Flight Date and Time Instructor Name C of G Weight and Balance Reference Graphs N8502V Seneca PA-34-200 Weight and Balance Reference Graphs N8502V Seneca PA-34-200 Weight and Balance Reference Graphs N8502V Seneca PA-34-200 C.G. Range and Weight Graph IT IS THE RESPONSIBILITY OF THE PILOT TO ASCERTAIN THAT THE AIRPLANE ALWAYS REMAINS WITHIN THE ALLOWABLE WEIGHT VS. CENTER OF GRAVITY ENVELOPE WHILE IN FLIGHT.

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