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 intended for pilots and aviation personnel to ensure safe loading and operation of the aircraft. The document outlines the maximum weight limits, center of gravity (CG) specifications, and procedures for calculating weight and balance before flight. Proper adherence to these guidelines is crucial for maintaining aircraft performance and safety during operations.
- Maximum takeoff weight: 3,800 lbs
- CG limits: 34.0 to 40.0 inches from datum
- Fuel weight: 6 lbs per gallon
- Proper weight distribution is crucial for safety
- Follow loading guidelines to maintain CG within limits.
Document
Source
Originally published by www.ninelima.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Pages
- 66
- File size
- 8.3 MB
- Publisher
- www.ninelima.org
Specifications & performance
Extracted from this document.
Specifications
- Empty weight (lb)
- 3,215
- Fuel capacity (gal)
- 93
- Max takeoff weight (lb)
- 4,407
Weight & balance
- Useful load (lb)
- 1,192
- Basic empty weight (lb)
- 3,215
- Max takeoff weight (lb)
- 4,407
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 Weight Limits
The maximum takeoff weight for the Piper PA-34 Seneca V is 3,800 lbs. This limit includes the weight of the aircraft, passengers, cargo, and fuel. Exceeding this weight can compromise aircraft performance and safety.
Center of Gravity Specifications
The center of gravity (CG) limits for the Piper PA-34 Seneca V are between 34.0 inches and 40.0 inches from the datum. It is essential to ensure that the CG remains within these limits for safe flight operations.
Weight Calculation Procedures
To calculate the weight and balance, pilots must account for the weight of each passenger, baggage, and fuel. The document provides a sample calculation to assist pilots in determining the total weight and CG position.
Loading Guidelines
Proper loading of the Piper PA-34 Seneca V is critical. The document details how to distribute weight evenly and avoid exceeding the maximum weight limits. It emphasizes the importance of placing heavier items in the front of the cabin to maintain CG within limits.
Fuel Load Considerations
The fuel capacity of the Piper PA-34 Seneca V is 110 gallons. Pilots should calculate the weight of the fuel (6 lbs per gallon) when determining the total weight and balance.
Safety notes
- Exceeding maximum weight can lead to performance issues.
- Ensure CG is within specified limits before flight.
Full document text
TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph Page No. No. 6.1 General 6-1 6.3 Airplane Weighing Procedure 6-2 6.5 Weight and Balance Data and Record. 6-5 6.7 General Loading Recommendations... 6-9 6.9 Weight and Balance Determination for Flight 6-10 6.11 6.13 Instructions for Using the Weight and Balance Plotter .. *Equipment List... 6-15 6-19 (a) Propeller and Propeller Accessories 6-20 (b) Engine and Engine Accessories 6-21 (c) Landing Gear and Brakes 6-22 (d) Electrical Equipment 6-23 (e) Instruments. 6-26 (f) Miscellaneous. 6-28 (g) Propeller and Propeller Accessories (Optional Equipment) …………. 6-29 (h) Engine and Engine Accessories (Optional Equipment).. 6-30 (i) Landing Gear and Brakes (Optional Equipment).. 6-31 (j) Electrical Equipment (Optional Equipment).. 6-32 (k) Instruments (Optional Equipment). 6-34 (1) Autopilots (Optional Equipment) 6-40 (m) Radio Equipment (Optional Equipment). 6-41 £ 6-55 6-65 ENCLOSED WITH THIS HANDBOOK (o) Miscellaneous (Optional Equipment) . Maximum Zero Fuel Weight Increase **Equipment List (Form 240 0017) *For 1982 and preceding models only. **For 1983 and subsequent models only. REPORT: VB-1150 6-i PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III SECTION 6 WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE 6.1 GENERAL In order to achieve the performance and flying characteristics which are designed into the airplane, it must be flown with the weight and center of gravity (C.G.) position within the approved operating range (envelope). Although the airplane offers flexibility of loading it cannot be flown with the maximum number of adult passengers, full fuel tanks and maximum baggage. With the flexibility comes responsibility. The pilot must insure that the airplane is loaded within the loading envelope before a takeoff. Misloading carries consequences for any aircraft. An overloaded air- plane will not take off, climb or cruise as well as a properly loaded one. The heavier the airplane is loaded, the less climb performance it will have. Center of gravity is a determining factor in flight characteristics. If the C.G. is too far forward in any airplane, it may be difficult to rotate for takeoff or landing. If the C.G. is too far aft, the airplane may rotate prematurely on takeoff or tend 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 airplane, however, will perform as intended. Before the airplane is licensed, it is weighed, and a basic empty weight and C.G. | location is computed (basic empty weight consists of the standard empty weight of the airplane plus the optional equipment). Using the basic empty weight and C.G. location, the pilot can easily determine the weight and C.G. position for the loaded airplane by computing the total weight and moment and then determining whether they are within the approved envelope. ISSUED: FEBRUARY 20, 1981 REVISED: SEPTEMBER 13, 1982 REPORT: VB-1150 6-1 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III The basic empty weight and C.G. location are recorded in the Weight and Balance Data Form (Figure 6-5) and the Weight and Balance Record (Figure 6-7). The current values should always be used. Whenever new equipment is added or any modification work is done, the mechanic responsible for the work is required to compute a new basic empty weight and C.G. position and to write these in the Aircraft Log Book and the Weight and Balance Record. The owner should make sure that it is done. A weight and balance calculation is necessary in determining how much fuel or baggage can be boarded so as to keep the C.G. within allowable limits. Check calculations prior to adding fuel to insure against improper loading. The following pages are forms used in weighing an airplane in production and in computing basic empty weight, C.G. position, and useful load. Note that the useful load includes usable fuel, baggage, cargo and passengers. Following this is the method for computing takeoff weight and C.G. 1 6.3 AIRPLANE WEIGHING PROCEDURES At the time of licensing, Piper Aircraft Corporation provides each air- plane with the basic empty weight and center of gravity location. This data is supplied by Figure 6-5. The removal or addition of equipment or airplane modifications can affect the basic empty weight and center of gravity. The following is a weighing procedure to determine this basic empty weight and center of gravity location: (a) Preparation (1) Be certain that all items checked in the airplane equipment list are installed in the proper location in the airplane. (2) Remove excessive dirt, grease, moisture, foreign items such as rags and tools from the airplane before weighing. (3) Defuel airplane. Then open all fuel drains until all remaining fuel is drained. Operate each engine until all undrainable fuel is used and engine stops. Then add the unusable fuel (5.0 gallons total, 2.5 gallons each wing). REPORT: VB-1150 6_27 ISSUED: FEBRUARY 20, 1981 DEVICED. SEPTEMRED 12 1087 PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III SECTION 6 WEIGHT AND BALANCE (4) Fill with oil to full capacity. (5) Place pilot and copilot seats in fourth (4th) notch, aft of forward position. Put flaps in the fully retracted position and all control surfaces in the neutral position. Tow bar should be in the proper location and all entrance and baggage doors closed. (6) Weigh the airplane inside a closed building to prevent errors in scale readings due to wind. (b) Leveling (1) With airplane on scales, block main gear oleo pistons in the fully extended position. (2) Level airplane (refer to Figure 6-3) deflating nose wheel tire, to center bubble on level. (c) Weighing - Airplane Basic Empty Weight (1) With the airpalne level and the brakes released, record the weight shown on each scale. Deduct the tare, if any, from each
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reading. Scale Position and Symbol Nose Wheel Right Main Wheel Left Main Wheel Basic Empty Weight, as Weighed Scale Reading Tare Net Weight (N) (R) (L) WEIGHING FORM Figure 6-1 ISSUED: FEBRUARY 20, 1981 REPORT: VB-1150 6-3 DATUM SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III (d) Basic Empty Weight Center of Gravity (1) The following geometry applies to the PA-34-220T airplane when it is level. Refer to Leveling paragraph 6.3 (b). C. G. ARM 78.4*- A = 25.3 B = 109.8 Level Points (Fuselage Left Side Below Window) B R + L *The datum is 78.4 inches ahead of the wing leading edge at the inboard edge of the inboard fuel tank. LEVELING DIAGRAM Figure 6-3 (2) The basic empty weight center of gravity (as weighed including optional equipment, full oil and unusable fuel) can be deter- mined by the following formula: C.G. ArmN (A) + (R + L) (B) inches T Where: TN + R + L REPORT: VB-1150 6-4 ISSUED: FEBRUARY 20, 1981 PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III SECTION 6 WEIGHT AND BALANCE 6.5 WEIGHT AND BALANCE DATA AND RECORD The Basic Empty Weight, Center of Gravity Location and Useful Load listed in Figure 6-5 are for the airplane as delivered from the factory. These figures apply only to the specific airplane serial number and registration number shown. The basic empty weight of the airplane as delivered from the factory has been entered in the Weight and Balance Record (Figure 6-7). This form is provided to present the current status of the airplane basic empty weight and a complete history of previous modifications. Any change to the perma- nently installed equipment or modification which affects weight or moment must be entered in the Weight and Balance Record. ISSUED: FEBRUARY 20, 1981 REPORT: VB-1150 6-5 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III Übertrag aus Flight-Manual Report Nr. VB-1110 MODEL PA-34-220T SENECA III 34-8133066 Airplane Serial Number Registration Number N 8372B OE-FEE Date 3-24-81 AIRPLANE BASIC EMPTY WEIGHT C.G. Arm Item Weight x (Inches Aft (Lbs.) of Datum) = Moment (In-Lbs.) Actual Standard Empty Weight* XXXXXXX 2855.5 86.1 245776 Optional Equipment 359.5 100.0 35962 Basic Empty Weight 3215.0 87.6 281738 *The standard empty weight includes full oil capacity and 5.0 gallons of unusable fuel. AIRPLANE USEFUL LOAD - NORMAL CATEGORY OPERATION (Gross Weight) - (Basic Empty Weight) = Useful Load (4407 lbs.) 3215.0 lbs.) = 1192.0lbs. THIS BASIC EMPTY WEIGHT, C.G. AND USEFUL LOAD ARE FOR THE AIRPLANE AS DELIVERED FROM THE FACTORY. REFER TO THE APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. WEIGHT AND BALANCE DATA FORM Figure 6-5 REPORT: VB-1150 6-6 ISSUED: FEBRUARY 20, 1981 PA-34-220T, SENECA III PIPER AIRCRAFT CORPORATION PA-34-220T Serial Number 34-8133066 Registration Number OE-FEE Date Item No. Description of Article or Modification Added (+) Removed (-) Weight Change Page Number Running Basic Empty Weight Moment 100 Wt. (Lb.) Arm (In.) Moment Wt. 100 (Lb.) 3/24 81 3215.0 281738 6.11:8||1 OPTIONAL EQUIPMENT 359.5 100.0 6.11.842 NEW OPT. EQUIPMENT GPS 100-ins, - 3P6.5 35P62 96.0 38064 3252.0 28385 Biter .95 3 ARS w/o 119.916 + 3.4 68.26 2.3207 3255.4 28403 22.11.96 3255,4 2840,770 WEIGHT AND BALANCE RECORD ISSUED: FEBRUARY 20, 1981 Figure 6-7 GPS 155 XL inst. 28.10.98 4 ARS Dien 0% 985562 As Weighed (weather radar 18.12.98 f removed) REPORT: VB-1150 6-7 3259.00 2843,0482 324243 28088363 AUST TROL SECTION 6 WEIGHT AND BALANCE 6-8 REPORT: VB-1150 PA-34-220T Serial Number Date Item No. WEIGHT AND BALANCE RECORD (cont) Figure 6-7 (cont) ISSUED: FEBRUARY 20, 1981 Description of Article or Modification Registration Number Wt. Weight Change (Lb.) Arm (In.) Moment 001 Removed (-) Added (+) Page Number Running Basic Empty Weight Wt. (L.b.) Moment 100 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III SECTION 6 WEIGHT AND BALANCE 6.7 GENERAL LOADING RECOMMENDATIONS The following general loading recommendation is intended only as a guide. The charts, graphs, instructions and plotter should be checked to assure the airplane is within the allowable weight vs. center of gravity envelope. (a) Pilot Only Load rear baggage compartment to capacity first. Without aft baggage, fuel load may be limited by forward envelope for some combinations of optional equipment. (b) 2 Occupants - Pilot and Passenger in Front Load rear baggage compartment to capacity first. Without aft | baggage, fuel load may be limited by forward envelope for some combinations of optional equipment. (c) 3 Occupants - 2 in front, 1 in middle Load rear baggage compartment to capacity first. Baggage in nose may be limited by forward envelope. Without aft baggage, fuel may be limited by forward envelope for some combinations of optional equipment. (d) 4 Occupants - 2 in front, 2 in middle Load rear baggage compartment to capacity first. Baggage in nose may be limited by forward envelope. Without aft baggage, fuel may be limited by forward envelope for some combinations of optional equipment. (e) 5 Occupants - 2 in front, 2 in middle, 1 in rear Investigation is required to determine optimum location for baggage. (f) 5 Occupants - 1 in front, 2 in middle, 2 in rear Load forward baggage to capacity first. Rear baggage and/or fuel load may be limited by aft envelope. (g) 6 Occupants - 2 in front, 2 in middle, 2 in rear With six occupants fuel and/or baggage may be limited by envelope load forward baggage compartment to capacity first. ISSUED: FEBRUARY 20, 1981 REVISED: JUNE 11, 1982 REPORT: VB-1150 6-9 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III (h) 7 Occupants - 2 in front, 3 in middle, 2 in rear With seven occupants fuel and/or baggage may be limited by envelope. For all airplane configurations, it is the responsibility of the pilot in command to make sure that the airplane always remains within the allowable weight vs. center of gravity envelope while in flight. 6.9 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. NOTES Actual fuel allowance for start-up, taxi and run-up (23 lbs. max.) should be determined based on local operating condition. Moment due to gear retraction does not signifi- cantly affect C.G. location. REPORT:VB-1150 6-10 ISSUED: FEBRUARY 20, 1981 DEVICED. A 1004 PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III SECTION 6 WEIGHT AND BALANCE Basic Empty Weight Pilot and Front Passenger Passengers (Center Seats) (Forward Facing) Passengers (Center Seats) (Aft Facing) (Optional) Arm Aft Weight Datum Moment (Lbs.) (Inches) (In-Lbs) 3212 88.5 284262 340.00 85.5 29070 118.1 119.1 Passengers (Rear Seats) 340.0 157.6 53585 Passenger (Jump Seat) (Optional) 118.1 Baggage (Forward) (100 Lbs. Max.) 35 22.5 788 Baggage (Aft) (100 Lbs. Max.) 178.7 Fuel (93 Gal. Max.) - Std. 480 93.6 44928 (123 Gal. Max.) - Opt. Takeoff Weight (4407 Lbs. Max.) (1999 Kg.) 4407 93.6 412633 The center of gravity (C.G.) of this sample loading problem is at 93.6 inches aft of the datum line. Locate this point (93.6) 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. Takeoff Weight (4407 Lbs. Max.) (1999 Kg.) Minus Estimated Fuel Burnoff 4407 93.6 412633 -360 93.6 -33696 Landing Weight (4407 Lbs. Max.) (1999 Kg.) 4047 93.6 378937 Locate the center of gravity for the landing weight on the C.G. range and weight graph. If this point falls within the weight C.G. envelope, the loading may be assumed acceptable for landing. IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY. SAMPLE LOADING PROBLEM Figure 6-9 ISSUED: FEBRUARY 20, 1981 REVISED: OCTOBER 31, 1986 REPORT: VB-1150 6-11 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III Basic Empty Weight Pilot and Front Passenger Passengers (Center Seats) (Forward Facing) Passengers (Center Seats) (Aft Facing) (Optional) Arm Aft Weight (Lbs.) Datum (Inches) Moment (In-Lbs) 85.5 118.1 119.1 Passengers (Rear Seats) 157.6 Passenger (Jump Seat) (Optional) 118.1 Baggage (Forward) (100 Lbs. Max.) 22.5 Baggage (Aft) (100 Lbs. Max.) 178.7 Fuel (93 Gal. Max.) - Std. 93.6 (123 Gal. Max.) - Opt. Takeoff Weight (4407 Lbs. Max.) (1999 Kg.) The center of gravity (C.G.) for the takeoff weight of the actual loading problem is at inches aft of the datum line. Locate this point ( ) on the C.G. range and weight graph. If this point falls within the weight - C.G. envelope, this loading meets the weight and balance requirements. Takeoff Weight (4407 Lbs. Max.) (1999 Kg.) Minus Estimated Fuel Burnoff Landing Weight (4407 Lbs. Max.) (1999 Kg.) 93.6 Locate the center of gravity for the landing weight on the C.G. range and weight graph. If this point falls within the weight C.G. envelope, the loading may be assumed acceptable for landing. IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY. WEIGHT AND BALANCE LOADING FORM Figure 6-11 REPORT: VB-1150 6-12 ISSUED: FEBURARY 20, 1981 REVISED: OCTOBER 31. 1986 LOAD (POUNDS) PIPER AIRCRAFT CORPORATION PA-34-220T, SENECA III 750 700 650 600 550 500 450 400 350 300 250 200 150 100 50 0 Forward Baggage- 10 10 15 20 Pilot and Front Passenger Aft Baggage Fuel (6 lb/gal). Center Passengers SECTION 6 WEIGHT AND BALANCE Aft Passengers' 225 25 30 35 40 45 50 55 60 65 70 MOMENT/1000 (POUND-INCHES) LOADING GRAPH Figure 6-13 ISSUED: FEBRUARY 20, 1981 REPORT: VB-1150 6-13