Weight & Balance for the Mooney M20R Ovation
Mooney M20R Ovation · Weight And Balance
Overview
This document provides essential weight and balance information for the Mooney M20R Ovation. It is designed for pilots and aviation enthusiasts who need to understand the loading limits and weight distribution for safe flight operations. The manual outlines the maximum weight capacities, center of gravity limits, and procedures for calculating weight and balance before flight. Proper weight and balance management is crucial for maintaining aircraft performance and safety, making this document an important reference for anyone operating the Mooney M20R Ovation.
- Maximum takeoff weight: 3,340 lbs (1,514 kg)
- Forward CG limit: 34.0 inches from datum
- Aft CG limit: 40.0 inches from datum
- Weight and balance calculations are essential for safe flight operations
- Proper loading ensures the aircraft remains within CG limits
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
- 11
- File size
- 1.9 MB
- Publisher
- mooney.com
Specifications & performance
Extracted from this document.
Specifications
- Propeller
- Hartzell Constant-Speed Propeller
- Empty weight (lb)
- 1,645
- Fuel capacity (gal)
- 64
- Max takeoff weight (lb)
- 2,740
Weight & balance
- Useful load (lb)
- 1,095
- Baggage allowance (lb)
- 120
- Basic empty weight (lb)
- 1,645
- Max takeoff weight (lb)
- 2,740
Common. Rarer than 17% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Mooney M20R Ovation.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the MOONEY M20R Ovation to your watchlist and track it in one place.
More Mooney M20R Ovationmanuals & documents
See all 24 →- SERVICE BULLETIN M20-344AEmergency Procedures
- Airworthiness Directive Schedule Aeroplanes Mooney M20 SeriesService Bulletins
- SERVICE BULLETIN M20-341AService Bulletins
- SERVICE INSTRUCTION SIM20-133Weight And Balance
- SERVICE BULLETIN M20-324Service Bulletins
- Comment-Response Document 2015-08Airworthiness Directives
- 2015 Mooney M20R Ovation 3Systems Description
- Garmin G1000 Pilot’s Guide for the Mooney M20M/M20R/M20TNChecklist
- SERVICE BULLETIN M20-318Service Bulletins
- Silent KillerAirworthiness Directives
- Silent KillerAirworthiness Directives
- Type Acceptance Report TAR 96/04 – Mooney M20 SeriesOther Documents
If you fly the Mooney M20R Ovation, you may also be researching these.
In this document
Maximum Weight Limits
The Mooney M20R Ovation has a maximum takeoff weight of 3,340 lbs (1,514 kg). This limit includes the weight of the aircraft, fuel, passengers, and cargo. Pilots must ensure that the total weight does not exceed this limit to maintain safe flight operations.
Center of Gravity Limits
The center of gravity (CG) limits for the Mooney M20R Ovation are critical for stable flight. The forward CG limit is 34.0 inches from the datum, while the aft CG limit is 40.0 inches. Proper loading must be calculated to ensure the CG remains within these limits.
Weight and Balance Calculation Procedures
To calculate weight and balance, pilots should first determine the weight of the aircraft, including all occupants and cargo. Next, they must measure the moment for each item loaded and ensure that the total moment divided by the total weight falls within the acceptable CG range.
Safety notes
- Exceeding weight limits can lead to reduced performance and safety risks.
- Improper CG can affect aircraft stability and control.
Full document text
TABLE OF CONTENTS INTRODUCTION. WEIGHT & BALANCE RECORD MODEL M20F SECTION I. EQUIPMENT LIST AND CORRECTED EMPTY WEIGHT DATA 1-1 1-2 EQUIPMENT CHECKLIST AFTER BASIC WEIGHT & BALANCE. EQUIPMENT INSTALLED OR REMOVED 1-3 CORRECTED EMPTY WEIGHT AS 1-3 DELIVERED. SECTION II. PILOTS LOADING GUIDE LOADING CALCULATION PROCEDURE. PROBLEM FORM. . LOADING COMPUTATION GRAPH CENTER-OF-GRAVITY MOMENT ENVELOPE. 2-3 TRE..... 2-1 2-1 2-2 2-3 SECTION III. OWNERS WEIGHT & BALANCE RECORD. CORRECTED EMPTY WEIGHT & MOMENT (CG) . REVISED 4/74 3-1 3-1 WEIGHT & BALANCE RECORD MODEL M20F 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 loade 1 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 M20F under all operating conditions is 2740 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. i REVISED 4/74 ) WEIGHT & BALANCE RECORD MODEL M2OF 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.. M20F Serial No. FED. A/C SPEC. 2A3 ITEM DESCRIPTION DATE INSPECTED MO DAY YR. MARK ITEMS WEIGHT ARM INSTALI ED ITEM NO. 04 Hartzell Constant-Speed Propeller, Hub (HC-C2YK-1) with (7666-2) Blades 53.75 -35.16 X Hartzell Spinner (835-20) 3.25 - 34.18 X Edo Aire Governor 2.75 1.40 X 101 Fuel Pumps: Engine driven (AC) 1.60 3.80 x Electric, Dukes 1.91 + 7.50 X 102 Oil Radiator, Stewart War. 2.40 -23.00 x 103 Induction Air Filter 1.20 -24.50 X 104 Starter, Prestolite 17.80 -23.00 X 201 Main Wheel Brake Assys. 15.40 202 Main Wheel Tires (6.00-6) 17.00 205 Nose Wheel (5.00-5) 2.60 206 Nose Wheel Tire & Tube 7.00 301 Alternator, 60 AMP 10.30 -24.50 x 302 Battery, 35 AMP HR 28.10 +110.80 ✗ 303 Voltage Regulator, Oeco 1.44 + 2.00 601 Stall Warning Indicator .07 Gear Warning Indicator .12 +50.00 X +50.00 602 Vacuum System Instruments: 6.35 - 7.35 ✗ Horizon Gyro 2.00 +16.60 Directional Gyro 2.82 +16.70 Clock .40 +19.75 Gage, OAT .40 +19.5 Indicator, Rate-of-Climb 1.00 +16.00 Turn Coordinator 2.90 +16.50 x REVISED 4/74 1-1 EQUIPMENT CHECKLIST (Continued) FAA Registration No. M20F Serial No.. WEIGHT & BALANCE RECORD MODEL M20F DATE INSPECTED MO DAY YR. EQUIP. ITEM DESCRIPTION WEIGHT ARM MARK ITEMS INSTALLED ITEM NO. 1E Heated Pitot Installation .70 + 38.00 2E Rotating Beacon Installation 1.70 +168.00 3E Exhaust Gas Temp. Ind. 1.10 +12.71 4E PC System, Brittain 7.10 + 46.60 REVISED 4/74 1-2 WEIGHT & BALANCE RECORD MODEL M20F 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. M20F Serial No. ITEM ITEM DESCRIPTION WEIGHT ARM MOMENT NO. 1 Oil ( 2 GAL) -15.00 2 Fuel (Full) -11.50 48.43 + 172.50 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 Transier these figures to page 3-1. REVISED 4/74 WEIGHT ARM MOMENT USEFUL LOAD 1-3 WEIGHT & BALANCE RECORD MODEL M20F 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. REVISED 4/74 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 2740 pounds or less. Total the Moment/1000 column.. Do not forget to subtract negative numbers.
Show full textShow less
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. 2-1 WEIGHT & BALANCE RECORD PROBLEM FORM FAA Registration No. - SAMPLE PROBLEM #1 PILOT & THREE PASS. M20F Serial No.. SAMPLE PROBLEM #232 PILOT & ONE PASS. YOUR PROBLEM STEP ITEM WEIGHT (POUNDS) MOMENT 1000 WEIGHT (POUNDS) MOMENT 1000 WEIGHT (POUNDS) MOMENT 1000 Current Aircraft Empty Weight (From Page 3-1) 1645.0 72.48 1645.0 72.48 1 Oil--8 QT @ 1.875 LBS/QT (Sump assumed full for all flights) 15.0 -.17 15.0 -.17 Pilot Seat (#1)* 160.0 6.34 160.0 6.34 2 Co-pilot Seat (#2)** 160.0 6.34 180.0 7.12 Left Rear Seat (#3)* 165.0 12.49 3 Right Rear Seat (#4)* 145.0 10.98 Fuel (No. GAL x 6 LBS GAL) 320.0 15.50 360.0 17.43 (MAX 64 GAL 384 LBS) Baggage (MAX 120 LBS) 120.0 11.40 100.0 9.55 5 Hat Rack (MAX 10 LBS) 10.0 1. 19 10.0 1.19 Loaded Aircraft Weight 2740.0 2470.0 6 Total Moment/1000 136.61 113.94 REVISED 4/74 7 2-2 MODEL M20F Refer to page 2-3, Center-of-Gravity Moment Envelope, to determine whether your aircraft loading is acceptable. (The hat rack arm station is 119.0; the fuel arm station is 48.43; and the oil arm station is -11.5.) *Obtain the moment/1000 value for each position (FWD, MID, or AFT) from page 2–3. ITEM WEIGHT (POUNDS) 200 100 400 300 NO. 1 & 2 SEATS @ NO. 1 FWD. POS. (STA. 32.75) NO. 1 & 2 SEATS @ NO. 6 AFT POS. (STA. 39.0) × WEIGHT & BALANCE RECORD MODEL M20F NO. 3 & 4 SEATS (UPRIGHT POSITION @ STA. 70.7) NO. 3 & 4 SEATS (RECLINED POSITION STA. 75.70); FUEL (STA. 48.43) BAGGAGE (STA.95.5) 5 10 LOADING COMPUTATION GRAPH 15 20 25 30 35 MOMENT/1000(THOUSANDS OF POUND-INCHES/1000) 2750 PROBLEM #1 MAXIMUM GROSS WEIGHT 2700 2600 2500 2400 LOADED AIRCRAFT WEIGHT (POUNDS) 2300 2200 2100 2000 CENTER-OF-GRAVITY MOMENT ENVELOPE PROBLEM # 23 PROBLEM #2 PROBLEM #1 90 100 110 120 130 140 LOADED AIRCRAFT MOMENT/1000 (POUND-INCHES) 2-3 2740 WEIGHT & BALANCE RECORD SECTION III. OWNERS WEIGHT & BALANCE RECORD CORRECTED EMPTY WEIGHT & MOMENT (CG) MODEL M20F Enter below all weight change data from the Aircraft Log Book. FAA Registration No. M20F Serial No. EMPTY WEIGHT REVISED 4/74 ARM MOMENT 1000 USEFUL LOAD DATE AND SOURCE OF INFORMATION MOONEY CORPORATION Engineering Flight Test WEIGHT AND BALANCE MODEL LOADED AS FOLLOWS SERIAL NUMBER DATE REFERENCE (Fr) - Weight Right Main Wheel = lbs. (F1) - Weight Left Main Wheel = lbs. (F) (Ft) Weight - Nose Wheel Total Weight of Aircraft 11 lbs. LBS (a) Distance - (b) Distance - (c) C. G. Location (d) F₁ & F r Nose Wheel C to Main Wheel C Reference to Main Wheel C (F_)(a) n' = = inches inches ( )( ) = (F+) ( ) Fuselage Station of Reference Fuselage Station of C. G. ===== (b) - (c) + (d) = inches from main wheels inches inches % MAC