Weight & Balance for the Piper PA-44 Seminole
Piper PA-44 Seminole · Weight And Balance
Overview
This document provides essential weight and balance information for the Piper PA-44 Seminole. It is designed for pilots and aviation personnel who need to ensure that the aircraft is loaded within its weight limits for safe operation. The document outlines the maximum weight capacities, loading procedures, and calculations necessary to maintain proper balance during flight. Understanding these parameters is crucial for flight safety and compliance with aviation regulations.
- Maximum takeoff weight: 4,800 lbs
- CG limits: 84.0 inches to 92.0 inches from the datum
- Weight calculation must include passengers, baggage, and fuel
- Proper loading is essential for maintaining balance
- Sample calculations help illustrate weight and balance procedures.
Document
Source
Originally published by www.panorama-air.de. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Pages
- 9
- File size
- 2.6 MB
- Publisher
- www.panorama-air.de
Specifications & performance
Extracted from this document.
Specifications
- Empty weight (lb)
- 1,181
- Fuel capacity (gal)
- 108
- Max takeoff weight (lb)
- 3,800
Performance
- Fuel burn (gph)
- 6
Weight & balance
- Max ramp weight (lb)
- 3,816
- Baggage allowance (lb)
- 200
- Basic empty weight (lb)
- 1,181
- Max takeoff weight (lb)
- 3,800
Most owners only have the POH. Here's the essential set for the Piper PA-44 Seminole.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
More Piper PA-44 Seminolemanuals & documents
See all 37 →- PILOT’S CHECKLISTPilot's Operating Handbook
- Multi-Engine Study GuideOther Documents
- Type Acceptance Report TAR 98/04 Rev 3Parts Catalog
- NSA Master Checklist Seminoles Fuel Injected Rev 12Checklist
- SERVICE BULLETIN NO. 1354Service Bulletins
- PA 44 Seminole Checklist (2126Y)Checklist
- Piper Seminole Normal ChecklistPilot's Operating Handbook
- Piper Seminole Training SupplementWeight And Balance
- Minimum Equipment List as a Mechanism of Motion in MIRCE MechanicsOther Documents
- PIPER PA-44 SEMINOLEChecklist
- TYPE-CERTIFICATE DATA SHEET No. EASA.IM.A.232 For Piper PA-44Pilot's Operating Handbook
- Garmin G1000 NXi Pilot’s Guide for the Piper PA-44-180 SeminoleV Speeds Reference
In this document
Maximum Weight Limits
The maximum takeoff weight for the Piper PA-44 Seminole is 4,800 lbs. This limit includes the weight of the aircraft, passengers, cargo, and fuel. It is critical to ensure that the total weight does not exceed this limit to maintain safe flight operations.
Center of Gravity (CG) Limits
The center of gravity limits for the Piper PA-44 Seminole are between 84.0 inches and 92.0 inches from the datum. Proper loading and weight distribution are necessary to keep the CG within these limits to ensure stable flight characteristics.
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 formula for calculating the total weight and the location of the CG based on the weights of the individual components.
Loading Procedures
The loading procedures section outlines how to properly load the aircraft to maintain balance. It includes guidelines on distributing weight evenly and securing cargo to prevent shifting during flight.
Sample Weight & Balance Calculation
A sample calculation is provided to illustrate how to determine the total weight and CG for a typical flight scenario. This example helps pilots understand the practical application of the weight and balance principles.
Safety notes
- Exceeding weight limits can lead to compromised flight performance.
- Improper CG can result in unstable flight characteristics.
Full document text
6-8 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-44-180, SEMINOLE PA-44-180 Date Item No. Serial Number 44-7995048 Registration Number D-6AFC Page Number 2 Description of Article or Modification 22.10. голо 07.10 2014 Schwerpunkt wägung Waging 105.11 2018 wägung Removed (-) (+) a 111 Weight Change Running Basic Empty Weight Wt. Arm Moment Wt. (Lb.) (In.) /100 (Lb.) Moment /100 kg Cinky 1178 256 468,5 1181,2 256 407,7 Kg mkg 1191 2582795 WEIGHT AND BALANCE RECORD (cont) REPORT: VB-860 Figure 6-7 (cont) ISSUED: MARCH 23, 1978 PIPER AIRCRAFT CORPORATION PA-44-180, SEMINOLE 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. ISSUED: MARCH 23, 1978 REVISED: MARCH 1, 1980 REPORT: VB-860 6-9 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-44-180, SEMINOLE Basic Empty Weight Pilot and Front Passenger Passengers (Rear Seats) Fuel (108 Gallon Maximum Usable) Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) 2515 $475 725725 340.0 80:5 27370 340.0 118.1 40154 240(40) 95.0 23000 142.8 Baggage (200 Lb. Limit)... Ramp Weight (3816 Lbs. Max.) Fuel Allowance for Engine Start, Taxi & Runup -16.0 95.0 -1520. Take-off Weight (3800 Lbs. Max.) The center of gravity (C.G.) for the take-off weight of this sample loading problem is at inches aft of the datum line. Locate this point ( ) 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. Take-off Weight Minus Estimated Fuel Burn-off (climb & cruise) @ 6.0 Lbs/Gal. 95.0 Landing Weight Locate the center of gravity of the landing weight on the C.G. range and weight graph. Since this point falls within the weight - C.G. envelope, the loading may be assumed acceptable for landing. IS LOADED IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE PROPERLY AT ALL TIMES. Leergewicht: 1181,2ky 07.10. Hebelaim 2014 Moment 2171 cm : 256 407, 7 cankey REPORT: VB-860 6-10 SAMPLE LOADING PROBLEM Figure 6-9 ISSUED: MARCH 23, 1978 REVISED: MARCH 1, 1980 PIPER AIRCRAFT CORPORATION PA-44-180, SEMINOLE SECTION 6 WEIGHT AND BALANCE . Basic Empty Weight Pilot and Front Passenger Passengers (Rear Seats) · Fuel (108 Gallon Maximum Usable) Baggage (200 Lb. Limit) ☑Ramp Weight (3816 Lbs. Max.) Weight (Lbs) Arm Aft Datum Moment (Inches) (In-Lbs) 80.5 118.1 95.0 142.8 Fuel Allowance for Engine Start, Taxi & Runup -16.0 95.0 -1520 Take-off Weight (3800 Lbs. Max.) The center of gravity (C.G.) for the take-off weight of this problem is at inches aft of the datum line. Locate this point ( loading ) 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. Take-off Weight Minus Estimated Fuel Burn-off (climb & cruise) @ 6.0 Lbs/Gal. Landing Weight 95.0 Locate the center of gravity of 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 AT ALL TIMES. WEIGHT AND BALANCE LOADING FORM ISSUED: MARCH 1, 1980 Figure 6-11 REPORT: VB-860 LOAD WEIGHT (POUNDS) PIPER AIRCRAFT CORPORATION PA-44-180, SEMINOLE 700 650 600 550 500 450 400 350 300 250 200 1550 100 50 FUEL (6 LB/GAL) PILOT AND FRONT PASSENGER AFT PASSENGERS BAGGAGE SECTION 6 WEIGHT AND BALANCE 0 0 1' 5 10 15 20 25 30 35 40 45 50 55 60 65 MOMENT/1000 (POUNDS-INCHES) LOADING GRAPH Figure 6-13 ISSUED: MARCH 23, 1978 REPORT: VB-860 6-11 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-44-180, SEMINOLE 3800 MAX. T.O. AND LANDING WEIGHT 89 90 91 92 93 88 3700- 87 3600 86 3500 85 +1 3400- 3300 3200 3100 3000 AIRCRAFT WEIGHT-LBS. 2900- 2800-84 2700 2600 2500 2400- 2300 FWD LIMIT 84 84 85 86 87 88 89 90 91 92 93 C.G. LOCATION (INCHES AFT DATUM) REPORT: VB-860 6-12 C.G. RANGE AND WEIGHT Figure 6-15 AFT LIMIT 93 ISSUED: MARCH 23, 1978 REVISED: MARCH 1, 1980 PIPER AIRCRAFT CORPORATION PA-44-180, SEMINOLE SECTION 6 WEIGHT AND BALANCE 6.9 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 any one of the loading slots over this point. Using a pencil, draw a line along the slot to the weight which
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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 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. ISSUED: MARCH 23, 1978 REPORT: VB-860 6-13 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-44-180, SEMINOLE SAMPLE PROBLEM A sample problem will demonstrate the use of the weight and balance plotter. 32Assume a basic weight and C.G. location of 2364 pounds at 86.14 inches respectively. We wish to carry a pilot and 3 passengers. Two men weighing 180 and 200 pounds will occupy the front seats, and two children weighing 80 and 100 pounds will ride in the rear. 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? (a) Place a dot on the plotter grid at 2364 pounds and 86.14 inches to represent the basic airplane. (See illustration.) (b) Slide the slotted plastic into position so that the dot is under the slot for the forward seats, at zero weight. (c) Draw a line up the slot to the 380 pound position (180 + 200) and put a dot. (d) Continue moving the plastic and plotting points to account for weight in the rear seats (80 + 100), baggage compartment (45), and fuel tanks (360). (e) As can be seen from the illustration, the final dot shows the total weight to be 3329 pounds with the C.G. at 89.30. This is well within the envelope. (f) 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-860 6-14 ISSUED: MARCH 23, 1978 PIPER AIRCRAFT CORPORATION PA-44-180, SEMINOLE SECTION 6 WEIGHT AND BALANCE SAMPLE PROBLEM MAX. T.O. AND 89 90 91 92 93 3800 LANDING WEIGHT 88 3700 87 3600 86 3500 85 3400- 3300 TAKEOFF WEIGHT AND C.G. 3200- 3100 3000 AIRCRAFT WEIGHT-LBS. 2900- 2800-84 2700 2600 2500 2400 2300 FWD LIMIT 84 BAGGAGE FUEL REAR SEATS FRONT SEATS BASIC WEIGHT AND C.G 84 85 86 87 88 89 90 91 92 93 C.G. LOCATION (INCHES AFT DATUM) AFT LIMIT 93 ISSUED: MARCH 23, 1978 REVISED: MARCH 1, 1980 REPORT: VB-860 6-15