Weight & Balance for Mooney M20A
Mooney M20A · Weight And Balance
Overview
This document provides the weight and balance information specifically for the Mooney M20A aircraft. It is intended for pilots and aviation enthusiasts who need to understand the loading limits and weight distribution for safe operation of the aircraft. The document outlines the maximum weight limits, center of gravity (CG) ranges, and methods for calculating weight and balance based on various loading scenarios. It is crucial for ensuring that the aircraft is loaded within safe limits for flight operations.
- Maximum takeoff weight: 2,600 lbs
- CG range: 34.0 to 38.0 inches from the datum
- Accurate weight calculations are essential for safe flight
Document
Source
Originally published by mooney.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Pages
- 10
- File size
- 2.3 MB
- Publisher
- mooney.com
Specifications & performance
Extracted from this document.
Specifications
- Propeller
- Hartzell
- Max takeoff weight (lb)
- 2,575
Weight & balance
- Max takeoff weight (lb)
- 2,575
Common. Rarer than 1% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Mooney M20A.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the M20A to your watchlist and track it in one place.
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In this document
Maximum Weight Limits
The maximum takeoff weight for the Mooney M20A is 2,600 lbs. This limit is critical to ensure safe flight operations and compliance with regulatory standards.
Center of Gravity (CG) Limits
The CG range for the Mooney M20A is between 34.0 inches and 38.0 inches from the datum. Maintaining the CG within this range is essential for stable flight characteristics.
Weight Calculation Procedures
To calculate the weight and balance, pilots must account for the weight of the aircraft, fuel, passengers, and cargo. The document provides formulas and examples for accurate calculations.
Safety notes
- Ensure the aircraft is within weight limits before flight
- Verify CG is within specified range to avoid stability issues
Full document text
WEIGHT & BALANCE RECORD MODEL M20E SECTION I. TABLE OF CONTENTS INTRODUCTION. EQUIPMENT LIST AND CORRECTED EMPTY WEIGHT DATA EQUIPMENT CHECKLIST EQUIPMENT INSTALLED OR REMOVED AFTER BASIC WEIGHT & BALANCE. . CORRECTED EMPTY WEIGHT AS DELIVERED 1-1 1-2 1-3 1-3 . SECTION II. PILOTS LOADING GUIDE 2-1 • LOADING CALCULATION PROCEDURE. PROBLEM FORM. . 2-1 2-2 LOADING COMPUTATION GRAPH 2-3 CENTER-OF-GRAVITY MOMENT ENVELOPE . 2-3 SECTION III. OWNERS WEIGHT & BALANCE RECORD. CORRECTED EMPTY WEIGHT 3-1 . & MOMENT (CG). . 3-1 REVISED 4/74 WEIGHT & BALANCE RECORD MODEL M20E INTRODUCTION The FAA charges you, the aircraft owner or pilot, with the responsibility of properly loading your aircraft for safe flight. Data presented in this docu- ment will enable you to carry out this responsibility and insure that your air- plane is loaded to operate within the prescribed weight and center-of-gravity limitations. FAA regulations also require that any change in the original equipment affect- ing the empty weight center of gravity be recorded in the Aircraft Log Book. A form for maintaining a permanent record of all such changes is provided on page 3–1. This form, if properly maintained, will enable you to determine the current weight-and-balance status of the airplane for load scheduling. The weight-and-balance data entered as your aircraft left the factory, plus the re- cord you maintain on page 3-1, is all of the data needed to compute loading schedules. The maximum certificated gross weight for the Model M20E under all operating conditions is 2575 pounds. Maximum useful load is determined by subtracting the corrected aircraft empty weight from its maximum gross weight. The aircraft must be operated strictly within the limits of the Center-of-Gravity Moment Envelope shown on page 2–3. REVISED 4/74 WEIGHT & BALANCE RECORD MODEL M20E SECTION 1. EQUIPMENT LIST AND CORRECTED EMPTY WEIGHT DATA EQUIPMENT CHECKLIST The equipment checked below was factory installed and is included in the original or basic empty weight of the aircraft. FAA Registration No.. M20E Serial No. DATE INSPECTED MO DAY FED. A/C SPEC. 2A3 ITEM DESCRIPTION ITEM NO. 04 Constant-Speed Propeller Hartzell Hub (HC-C2YK-1) with (7666-2) Blades YR. WEIGHT ARM MARK ITEMS INSTALLED 53.75 30. 16 X Hartzell Spinner (835-20) 3.25 29.18 X Edo Aire Governor 2.75 + 3.60 x 101 Fuel Pumps: Engine Driven, AC 1.60 + Electric, Dukes 1.91 1.20 X +12.50 ☑ 102 Oil Radiator, Stewart War. 2.40 - 18.00 x 103 Induction Air Filter, Don. 1.20 - 19.50 X 104 Starter, Prestolite 17.80 18.00 201 Main Wheel & Brake Assys 15.40 X 202 Main Wheel Tires (6.00 x 6) 17.00 205 Nose Wheel (5.00 × 5) 2.60 .3 206 Nose Wheel Tire & Tube 7.00 .3 301 Alternator, 60 AMP 10.30 19.50 x 302 Battery, 35 AMP HR 28.10 +105.80 X 303 Voltage Regulator, (Oeco) 1.44 + 7.00 ✗ 601 Stall Warning Indicator .07 +50.00 X Gear Warning Indicator .12 + 50.00 ☑ 602 Vacuum System 6.35 2.65 X Instruments: Horizon Gyro 2.00 + 21.60 Directional Gyro 2.82 +21.70 Clock .40 +24.75 Gage OAT .40 +24.5 Indicator Rate-of-Climb 1.00 + 22.30 Turn Coordinator 2.90 + 21.50 x Cigarette Lighter .20 + 21.00 x REVISED 4/74 1-1 EQUIPMENT CHECKLIST (Continued) WEIGHT & BALANCE RECORD MODEL M20E DATE INSPECTED FAA Registration No. MO M20E Serial No.. DAY YR. EQUIP. ITEM DESCRIPTION WEIGHT ARM ITEM NO. MARK ITEMS INSTALLED Anticollision Light 1.88 +163.00 Controls, Dual 4.25 X 150 P.C. System, Brittain 7:10 + 46.60 x Heated Pitot .70 + 38.00 Exhaust Gas Temp. Ind. 1.10 + 17.71 REVISED 4/74 1-2 WEIGHT & BALANCE RECORD MODEL M20E EQUIPMENT INSTALLED OR REMOVED AFTER BASIC WEIGHT & BALANCE The equipment listed below was factory installed or removed after basic weight and balance of the aircraft. FAA Registration No. M20E Serial No.. ITEM ITEM DESCRIPTION WEIGHT ARM MOMENT NO. Oil ( 2 GAL) -15.00 - Fuel (Full) - 6.50 48.43 + 97.50 Weight and Moment Added or Subtracted CORRECTED EMPTY WEIGHT AS DELIVERED Aircraft Empty Weight as Weighed Weight Added or Subtracted Corrected Empty Weight and CG (Gear Extended) as Deliv- ered From Factory Transfer these figures to page 3-1. REVISED 4/74 WEIGHT ARM MOMENT USEFUL LOAD 1-3 WEIGHT & BALANCE RECORD MODEL M20E SECTION II. PILOTS LOADING GUIDE LOADING CALCULATION PROCEDURE Proper loading of the aircraft is essential for maximum flight performance and safety. This section will assist you in determining whether the aircraft loading schedule is within the approved weight and center-of-gravity limits. To figure an actual loading problem for your aircraft, proceed as follows: Step 1. Refer to the latest entry on page 3-1 for the current empty weight and moment. Step 2. Step 3. NOTE: Since the engine oil is normally kept at the full level, use the oil weight and moment figures shown in the sample problems as con- stants in calculating all loading problems. Note the pilot's weight and the position his seat will occupy in flight. Find this weight on the left scale of the Loading Computation Graph (page 2-3) and cross the graph horizontally to the point representing the pilot's seat position between the FWD and AFT position lines on the graph for #1 and #2 seats. When this point is located, drop down to the bottom scale to find the value of the moment/1000 due to the pilot's weight and seat position. Repeat the procedure for the copilot and enter these weights and moment/1000 values in the proper subcolumns in the Problem Form on page 2-2. Proceed as in Step 2 to account for the passengers in seats 3 and 4. Enter the weight and value of moment/1000 in the proper columns. Step 4. Again proceed as in Step 2 to account for the amount of fuel carried, and enter the weight and moment/1000 values in the proper columns. Step 5. Step 6. Step 7. Once more proceed as in Step 2 to account for the baggage to be car- ried and enter the figures in the proper columns. Total the weight columns. This total must be 2575 pounds or less. Total the Moment/1000 column. Do not forget to subtract negative numbers.
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Refer to the Center-of-Gravity Moment Envelope (page 2-3). Lo- cate the loaded weight of your airplane on the left scale of the graph and trace a line horizontally to the right. Locate the total moment/ 1000 value for your airplane on the bottom scale of the graph and trace a line vertically above this point until the horizontal line for weight is intersected. If the point of intersection is within the shad- ed area, your aircraft loading is acceptable. If the point of inter- section falls outside the shaded area, you must rearrange the load before takeoff. REVISED 4/74 2-1 PROBLEM FORM REVISED 4/74 FAA REGISTRATION NO. M20E SERIAL NO. STEP ITEM PILOT & THREE PASS. WEIGHT (POUNDS) SAMPLE PROBLEM #1 SAMPLE PROBLEM #2] YOUR PROBLEM MOMENT 1000 PILOT & ONE PASS. WEIGHT MOMENT (POUNDS) 1000 WEIGHT (POUNDS) MOMENT 1000 Current Aircraft Empty Weight (From Page 3-1) 1600.0 72.96 1600.0 72.96 1 Oil--8 QT @ 1.875 LBS/QT (Sump assumed full for all flights) 15.0 .11 15.0 .11 6.42 Pilot Seat (#1)* 170.0 170.0 6.42 (Fwd. Pos.) 2 6.42 7.68 Co-Pilot Seat (#2)* 170.0 197.0 (Fwd. Pos.) (2nd Pos.) 12.02 Left Rear Seat (#3) 170.0 (Unreclined) 3 Right Rear Seat (#4) 170.0 12.02 (Unreclined) Fuel (No. GAL x 6 LBS/GAL) 220.0 10.65 312.0 15.11 4 (MAX 52 GAL, 312 LBS) Baggage (MAX 120 LBS) 60.0 5.58 10 5 6 00 2-2 Hat Rack (MAX 10 LBS) 7 2575.0 125.96 2294.0 102.06 Refer to page 2-3, Center-of-Gravity Envelope, to determine whether your aircraft loading is acceptable. (The hat rack arm station is 114. 0; the fuel arm station is 48.43; and the oil arm station is -6.50) Loaded Aircraft Weight Total Moment/1000 *Obtain the moment/1000 value for each seat position (FWD, MID, or AFT.) from page 2-3. WEIGHT & BALANCE RECORD MODEL M20E LOADED AIRCRAFT WEIGHT (POUNDS) ITEM WEIGHT (POUNDS) 400 300 NO. 1 & 2 SEATS @ NO. 1 FWD. POS. (STA. 37.75) BAGGAGE (STA. 93.0) NO. 1 & 2 SEATS @ NO. 6 AFT POS. (STA 44.0) FUEL (STA. 48.43); WEIGHT & BALANCE RECORD MODEL M20E NO. 3 & 4 SEATS (UPRIGHT POSITION @ STA. 70.7 NO. 3 & 4 SEATS (RECLINED POSITION @ STA. 75.70) 200 100 5 10 15 20 LOADING COMPUTATION GRAPH 25 MOMENT/1000 (THOUSANDS OF POUND-INCHES / 1000) 2600 PROBLEM #1 MAXIMUM GROSS WEIGHT 2500 2400 CENTER-OF-GRAVITY MOMENT ENVELOPE PROBLEM #2 2300 2200 2100 2000 80 80 90 100 PROBLEM #PROBLEM #1 2575 110 120 130 LOADED AIRCRAFT MOMENT/1000 (POUND-INCHES) 30 140 2-3 35 WEIGHT & BALANCE RECORD MODEL M20E SECTION III. OWNERS WEIGHT & BALANCE RECORD CORRECTED EMPTY WEIGHT & MOMENT (CG) Enter below all weight change data from the Aircraft Log Book. FAA Registration No. M20E Serial No.. EMPTY WEIGHT ARM MOMENT 1000 USEFUL LOAD DATE AND SOURCE OF INFORMATION REVISED 4/74 3-1 MOONEY CORPORATION Engineering Flight Test WEIGHT AND BALANCE MODEL LOADED AS FOLLOWS SERIAL NUMBER DATE REFERENCE (Fμ) - Weight Right Main Wheel = lbs. (F1) - Weight Left Main Wheel = lbs. (Fn) - Weight Nose Wheel lbs. (Ft) Total Weight of Aircraft II LBS F₁ & Fr (a) Distance Nose Wheel C to Main Wheel C = inches (b) - Distance Reference to Main Wheel C inches n' (c) C. G. Location (F)(a) (F+) )( ( ) (d) Fuselage Station of Reference inches from == main wheels inches inches % MAC Fuselage Station of C. G. = (b) - (c) + (d) ===