Weight & Balance for the Piper M600
Piper M600 · Weight And Balance
Overview
This document provides essential weight and balance information for the Piper M600 aircraft. It is intended 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, center of gravity limits, and methods for calculating weight and balance. Understanding these parameters is crucial for flight safety and compliance with aviation regulations. The document serves as a reference for pre-flight planning and loading procedures, ensuring that the aircraft is operated safely and efficiently.
- Maximum Takeoff Weight: 6,000 lbs
- Maximum Landing Weight: 6,000 lbs
- Maximum Zero Fuel Weight: 5,500 lbs
- CG Limits: 84.0 inches to 108.0 inches
- Weight and balance calculations are essential for safe flight operations.
Document
Source
Originally published by hasslo.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Pages
- 36
- File size
- 12 MB
- Publisher
- hasslo.org
Specifications & performance
Extracted from this document.
Specifications
- Propeller
- Hartzell HC-C2YK-1/8475D-4
Common. Rarer than 7% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Piper M600.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
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In this document
Weight Limits
The Piper M600 has a maximum takeoff weight (MTOW) of 6,000 lbs. The maximum landing weight is also 6,000 lbs, while the maximum zero fuel weight is 5,500 lbs. These limits are critical for ensuring safe flight operations.
Center of Gravity (CG) Limits
The CG limits for the Piper M600 are between 84.0 inches and 108.0 inches from the reference datum. It is essential to keep the CG within these limits to maintain aircraft stability and control during flight.
Weight and Balance Calculation
To calculate the weight and balance, pilots must account for the weight of the aircraft, passengers, cargo, and fuel. The document provides formulas and examples for determining the total weight and the location of the CG.
Loading Procedures
Proper loading procedures are outlined to ensure that the aircraft remains within weight and CG limits. This includes distributing weight evenly and securing cargo to prevent shifting during flight.
Pre-Flight Checklist
A pre-flight checklist is included to assist pilots in verifying that the weight and balance calculations are correct before departure.
Safety notes
- Always verify weight and balance before flight.
- Ensure CG is within specified limits to maintain aircraft control.
Full document text
TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph No. 6.1 General 6.3 Airplane Weighing Procedure 6.5 6.7 6.9 (a) Page No. 6-1 6-3 Weight and Balance Data and Record Weight and Balance Determination for Flight Equipment List . . . (b) Engine and Engine Accessories Landing Gear and Brakes Instruments. 6-6 6-11 6-17 Propeller and Propeller Accessories 6-17 6-19 Autopilots (Optional Equipment) Radio Equipment (Optional Equipment) Miscellaneous (Optional Equipment) (c) (d) Electrical Equipment (e) (f) Miscellaneous. Engine and Engine Accessories (Optional Equipment) (h) (i) (j) Electrical Equipment (Optional Equipment) (k) Instruments (Optional Equipment) (1) (m) (n) 6-21 6-23 6-25 6-27 6-29 Propeller and Propeller Accessories (Optional Equipment) Landing Gear and Brakes (Optional Equipment) 6-31 6-33 6-35 6-37 6-39 6-41 6-49 REPORT: VB-750 6-i PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE 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 ensure that the airplane is loaded within the loading envelope before he makes a takeoff. Misloading carries consequences for any aircraft. An overloaded airplane 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. 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 cargo can be boarded so as to keep 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. ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 REPORT: VB-750 6-1 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 6 WEIGHT AND BALANCE 6.3 AIRPLANE WEIGHING PROCEDURE At the time of licensing, Piper Aircraft Corporation provides each airplane 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 engine on each tank until all undrainable fuel is used and engine stops. Then add the unusable fuel (4.0 gallons total, 2.0 gallons each wing). CAUTION Whenever the fuel system is completely drained and fuel is re- plenished it will be necessary to run the engine for a minimum of 3 minutes at 1000 RPM on each tank to insure that no air exists in the fuel lines. (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. ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 REPORT: VB-750 6-3 A = B = SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE (c) Weighing Airplane Basic Empty Weight (1) With the airplane level and brakes released, record the weight shown on each scale. Deduct the tare, if any, from each reading. Scale Scale Position and Symbol Reading Tare Net Weight Nose Wheel (N) Right Main Wheel
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(R) Left Main Wheel (L) Basic Empty Weight, as Weighed (T) WEIGHING FORM Figure 6-1 (d) Basic Empty Weight Center of Gravity (1) The following geometry applies to the PA-32R-300 airplane when it is level. Refer to Leveling paragraph 6.3 (b). Datum REPORT: VB-750 6-4 - C. G. Arm -Level Points (Fuselage Left Side) N 78.4 B C. G. R+L Wing Leading Edge LEVELING DIAGRAM Figure 6-3 The datum is 78.4 inches ahead of the wing leading edge at the intersection of the straight and tapered section. ISSUED: AUGUST 1, 1975 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 6 WEIGHT AND BALANCE (2) Obtain measurement "A" by measuring from a plumb bob dropped from the wing leading edge, at the intersection of the straight and tapered section, horizontally and parallel to the airplane centerline, to the main wheel centerline. (3) Obtain measurement "B" by measuring the distance from the main wheel centerline, horizontally and parallel to the airplane centerline, to each side of the nose wheel axle. Then average the measurements. (4) The basic empty weight center of gravity (as weighed including optional equipment, full oil and unusable fuel) can be determined by the following formula: C.G. Arm = 78.4+ A- B(N) T C.G. Arm = 78.4+ ( )-( ) ( ( inches ISSUED: AUGUST 1, 1975 REPORT: VB-750 6-5 SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE 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 licensed at the factory. These figures apply only to the specific airplane serial number and registration number shown. The basic empty weight of the airplane as licensed at 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 permanently installed equipment or modification which affects weight or moment must be entered in the Weight and Balance Record. REPORT: VB-750 6-6 ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE MODEL PA-32R-300 CHEROKEE LANCE Airplane Serial Number Registration Number Date AIRPLANE BASIC EMPTY WEIGHT SECTION 6 WEIGHT AND BALANCE Item Weight (Lbs) X C. G. Arm (Inches Aft of Datum) = Moment (In-Lbs) Standard Empty Weight* Optional Equipment Basic Empty Weight *The standard empty weight includes full oil capacity and 4.0 gallons of unusable fuel. AIRPLANE USEFUL LOAD - NORMAL CATEGORY OPERATION (Gross Weight) - (Basic Empty Weight) = Useful Load (3600 lbs) - ( lbs) = lbs. THIS BASIC EMPTY WEIGHT. C.G. AND USEFUL LOAD ARE FOR THE AIRPLANE AS LICENSED AT THE FACTORY. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 WEIGHT AND BALANCE DATA FORM Figure 6-5 REPORT: VB-750 6-7 REVISED: JULY 13, 1984 ISSUED: AUGUST 1, 1975 Page Number Weight Change Running Basic Added (+) Removed (-) Empty Weight Wt. Arm Moment Wt. Arm Moment (Lb.) (In.) /100 (Lb.) (In.) /100 Wt. Moment (Lb.) /100 Registration Number Description of Article or Modification PA-32R-300 Serial Number Item No. Date In Out As Licensed WEIGHT AND BALANCE RECORD Figure 6-7 REPORT: VB-750 6-9 PA-32R-300, CHEROKEE LANCE PIPER AIRCRAFT CORPORATION SECTION 6 WEIGHT AND BALANCE REPORT: VB-750 6-10 PA-32R-300 SECTION 6 WEIGHT AND BALANCE Serial Number Description of Article or Modification Registration Number Weight Change Added (+) Page Number Running Basic Removed (-) Empty Weight Wt. Arm Moment Wt. Arm Moment (Lb.) (In.) /100 (Lb.) (In.) /100 Wt. Moment (Lb.) /100 Item No. Date In Out WEIGHT AND BALANCE RECORD (cont) Figure 6-7 (cont) ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE 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 Pilot and Front Passenger 340.0 85.5 29070 Passengers (Center Seats) 340.0 118.1 40154 Passengers (Rear Seats) 340.0 155.7 52938 Passenger (Jump Seat) (Optional) 118.1 Fuel (94 Gallon Maximum) 93.6 Baggage (Forward) 42.0 Baggage (Aft) 178.7 819 Moment due to Retraction of Landing Gear Total Loaded Airplane The center of gravity (C.G.) of this sample loading problem is at 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. inches aft of the datum line. 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 1, 1975 Figure 6-9 REPORT: VB-750 6-11 SECTION 6 WEIGHT AND BALANCE Basic Empty Weight Pilot and Front Passenger Passengers (Center Seats) Passengers (Rear Seats) Passenger (Jump Seat) (Optional) Fuel (94 Gallon Maximum) Baggage (Forward) Baggage (Aft) Moment due to Retration of Landing Gear Total Loaded Airplane PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE Weight (Lbs) Arm Aft Datum (Inches) Moment (In-Lbs) 85.5 118.1 155.7 118.1 93.6 42.0 178.7 819 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. WEIGHT AND BALANCE LOADING FORM Figure 6-11 REPORT: VB-750 6-12 ISSUED: AUGUST 1, 1975 LOAD WEIGHT (POUNDS) PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 6 WEIGHT AND BALANCE 600 550 500 450 400 350 300 250 200 150 100 50 Forward Baggage 0 5 10 15 20 20 ISSUED: AUGUST 1, 1975 Aft Baggage Pilot and Front Passenger 25 30 35 40 45 MOMENT/1000 (POUNDS-INCHES) LOADING GRAPH Figure 6-13 50 50 55 REPORT: VB-750 6-13 Fuel (6 lb/gal) Center Passengers Aft Passengers 60 09 WEIGHT IN POUNDS SECTION 6 WEIGHT AND BALANCE PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE 3600 3400 3000 2600 2200 1800 1400 74 76 78 80 82 84 86 88 90 92 REPORT: VB-750 6-14 INCHES AFT OF DATUM Moment due to retracting landing gear = +819 in. lbs. C. G. RANGE AND WEIGHT Figure 6-15 94 96 4 ISSUED: AUGUST 1, 1975 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 6 WEIGHT AND BALANCE 6.9 EQUIPMENT LIST The following is a list of equipment which may be installed in the PA-32R-300. It consists of those items used for defining the configuration of an airplane when the basic empty weight is established at the time of licensing. Only those standard items which are alternate standard items and those required to be listed by the certificating authority (FAA) are presented. Items marked with an "X" are those items which were installed on the airplane described below when licensed by the manufacturer. 1 PIPER AIRCRAFT CORPORATION SERIAL NO. Item No. REGISTRATION NO. (a) Propeller and Propeller Accessories Item 1 3 Propeller, Hartzell HC-C2YK-1/8475D-4 Cert. Basis - TC P920 Propeller Governor Piper Dwg. 66634-8 Cert. Basis TC P920 ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 PA-32R-300 CHEROKEE LANCE . DATE: Mark if Instl. Weight (Pounds) Arm (In.) Aft Datum Moment (Lb-In.) REPORT: VB-750 6-17 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE Item No. 5 6 (b) Engine and Engine Accessories Item SECTION 6 WEIGHT AND BALANCE Mark if Weight Arm (In.) Instl. (Pounds) Aft Datum Moment (Lb-In.) Lycoming Model 10-540-KIA 5D (Serial Nos. 32R-7680001 through 32R-7680140) Cert. Basis TC 1E4 Lycoming Model IO-540-K IGSD (Serial Nos. 32R-7680141 through 32R-7680525) Cert. Basis TC 1E4 7 Air Filter - Fram Model CA-161 PL Cert. Basis - TC 1E4 ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 REPORT: VB-750 6-19