Weight & Balance for Mooney M20C Ranger

***Removed After Production Weight & Balance ****See Weight & Balance Data of Aircraft for Wheel and Tire Locations Page 4 Mooney Aircraft, Inc. MOONEY MODEL M20C (1966) ACTUAL WEIGHT & BALANCE DATA F.A.A. Registration No. 6. EMPTY WEIGHT & C.G. COMPUTATIONS: Horiz. Datum (Fus. Sta. 0) Pilot C.G. Range Aircraft Empty Weight C.G. 36.5 44.0 Kerrville, Texas Date Leveling Surface (Skin line over radio access panel) Item Right Main Wheel Left Main Wheel Nose Wheel Empty Wt. as Weighed Weight Horizontal Datum is Centerline of Nose Gear Support Bolts (Sta. 0) and is 33.0" forward of Wing L.E. at Wing Sta. 59.25 (Inboard edge of stall strip). MAC is 59.2". L.E. of MAC is 33.1" aft Datum. Leveling means: Edge of skin splice over aft fuselage radio access panel. (Spirit level is used to level.) Computations: C.G. Forward of Main Wheels = Χ C.G. Aft Datum = C.G. % MAC = 1 33.1)/59.2 = "; 59.2 = MAC The Empty Weight C.G. location is with the landing gear extended and with both front seats in the forward location (40.0"). Each seat weighs 17.0 pounds. Maximum seat travel is 7.5" in 6 equal adjustments. Moment change per seat in aft position (47.5") is 128 inch-pounds. Page 5 Mooney Aircrait, inc. MOONEY MODEL M20C (1966) ACTUAL WEIGHT & BALANCE DATA F.A.A. Registration No. 7 LOADING SCHEDULE: Kerrville, Texas Date The following information is offered as an aid in checking loadings without having to perform the computations shown on Page 2. These loadings are all based on an average passenger or pilot weight of 170 pounds and it is assumed that the forward seats are in the second position aft. If the actual loading does not correspond to one of the basic loading conditions, then a detailed check should be made according to the procedure shown on Page 2. For normal usage, there are five basic loadings for this airplane. They are: Loading #1 Pilot alone Loading #2 Pilot and front passenger Loading #3 Loading #34 Pilot, front passenger and one rear passenger Pilot and 3 passengers Loading #5 Pilot, 3 passengers and 10 lbs. in hatrack Loadings #1 and #2 are not limited in any way. The maximum fuel, baggage, and hatrack loads can be carried without exceeding either gross weight or C.G. limits. Loading #3 is not limited as far as C.G. is concerned. However, it is possible to exceed the gross weight if the empty, equipped weight of the airplane exceeds 1608 pounds. Loadings #4 and #5 are limited as shown in the graph below. 120 (Max) 110 L100 28262 23 2 40 20 ALLOWABLE BAGGAGE (POUNDS) 30 #35. Pilot, 3 Passengers, & 10 lbs. on hat- rack 10 % Pilot and 3 passengers 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 Loading #4: take-off fuel with ALLOWABLE FUEL AT TAKE-OFF (POUNDS) 1880 empty wt. == -- # baggage 1830 Loading #5: *Note: fuel with no baggage take-off fuel with fuel with no baggage Max. baggage for Loading #35 == ===== 1870 - empty weight # baggage* = 1870 - - Lbs. (max.) empty wt. lbs. (Max.) -- empty wt. = lbs. (Max.) lbs. (Max.) is 15 lbs. less than max. baggage for Loading #4. Page 6 WEIGHT & BALANCE RECORD MODEL M20C 1966 & ON TABLE OF CONTENTS SECTION I. INTRODUCTION EQUIPMENT LIST AND CORRECTED EMPTY WEIGHT DATA EQUIPMENT CHECKLIST. EQUIPMENT INSTALLED OR REMOVED AFTER BASIC WEIGHT & BALANCE. CORRECTED EMPTY WEIGHT AS 1-1 ° 1-1 1-3 DELIVERED. 1-3 SECTION II. PILOTS LOADING GUIDE 2-1 LOADING CALCULATION PROCEDURE PROBLEM FORM 2-1 2-2 LOADING COMPUTATION GRAPH CENTER-OF-GRAVITY MOMENT ENVELOPE SECTION III. OWNERS WEIGHT & BALANCE RECORD CORRECTED EMPTY WEIGHT & MOMENT (CG) . 2-3 2-3 3-1 ° 3-1 REVISED 10/78 EQUIPMENT CHECKLIST (Continued) FAA Registration No. M20C Serial No. WEIGHT & BALANCE RECORD MODEL M20C MO DATE INSPECTED DAY YR. FED. A/C SPEC 2A3 MARK ITEMS ITEM DESCRIPTION WEIGHT ARM INSTALLED ITEM NO. Anticollision Light 1.70 +163.00 Controls, Dual 4.25 15.0 P.C. System, Brittain 7.10 + 46.40 Heated Pitot Inst. .70 + 38.00 Exhaust Gas Temp. Ind. 1.10 + 17.71 ☑☑ REVISED 10/78 1-2 WEIGHT & BALANCE RECORD MODEL M20C 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. M20C Serial No. ITEM ITEM DESCRIPTION NO. 1 Oil (2 GAL) 2 Fuel (Full) WEIGHT ARM MOMENT - 15.00 - 7.40 +111.00 48.43 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.) WEIGHT ARM MOMENT USE FUL LOAD 1-3 REVISED 10/78 WEIGHT & BALANCE RECORD MODEL M20C 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. Step 2. Step 3. Step 4. Step 5. Step 6. Step 7. Refer to the latest entry on page 3-1 for the current empty weight and moment. 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. 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. 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. 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 shaded area, your aircraft loading is acceptable. If the point of intersection falls outside the shaded area, you must rearrange the load before takeoff. REVISED 10/78 2-1 MODEL M20C WEIGHT & BALANCE RECORD PROBLEM FORM FAA Registration No. STEP ITEM Current Aircraft Empty Weight (From Pg. 3-1) 1566.0 MOMENT 1000 70.63 M20C Serial No. SAMPLE PROBLEM #1 PILOT & ONE PASS. (Seats Fwd. Position) WEIGHT (POUNDS) SAMPLE PROBLEM #2 PILOT & THREE PASS. YOUR PROBLEM 1566.0 WEIGHT MOMENT (POUNDS) 1000 70.63 WEIGHT MOMENT (POUNDS) 1000 Oil--8 QT @ 1.875 LBS/QT 15.0 -.11 15.0 -.11 (Sump assumed full for all flights) Pilot Seat (#1)* 170.0 6.42 170.0 (Fwd. Pos.) 6.42 (Fwd. Pos.) 2 Co-pilot Seat (#2)* 170.0 6.63 170.0 (2nd Pos.) 6.42 (Fwd. Pos. Left Rear Seat (#3)* 170.0 12.02 (Unreclined) 3 Right Rear Seat (#4)* 170.0 12.02 (Unreclined) Fuel (No. GAL × 6 LBS GAL) (MAX 52 GAL 312 LBS) 312.0 15.11 234.0 11.33 5 Baggage (MAX 120 LBS) 80.0 7.44 Loaded Aircraft Weight 2233.0 2575.0 6 Total Moment/1000 98.68 126.17 7 Refer to page 2-3, Center-of-Gravity Moment Envelope, to determine whether your aircraft loading is acceptable. (The fuel arm station is 48.43, the oil arm station is -7.4 and the hatrack station is 114. 0 Max. 10 lbs.) *Obtain the moment/1000 value for each position (FWD, MID, or AFT) from page 2-3. REVISED 10/78 2-2 10/78 LOADED AIRCRAFT WEIGHT (POUNDS) T (POUNDS) ITEM WEIGHT ( 400 300 200 100 WEIGHT & BALANCE MODEL M20C NO.1&2 SEATS @ NO.1 FWD. POS. (STA.37.75) NO.1&2 SEATS @ NO. 6 AFT POS.(STA.44.0) FUEL (STA. 48.43) NO. 3 & 4 SEATS (UPRIGHT POSITION) @STA. 70.7. BAGGAGE (STA. 93.0) 5 NO. 3 & 4 SEATS (RECLINED POSITION @ STA. 75.70) 10 15 LOADING COMPUTATION GRAPH 20 25 30 35 MOMENT/1000 (THOUSANDS OF POUND-INCHES/1000) 2600 PROBLEM #2' MAXIMUM GROSS WEIGHT F 2575 2500 2400 2300 CENTER-OF-GRAVITY MOMENT ENVELOPE 2200 PROBLEM #1 2100 2000 80' 90 100 110 PROBLEM EM #2 120 130 140 LOADED AIRCRAFT MOMENT/1000 (POUND-INCHES) 2-3 WEIGHT & BALANCE RECORD MODEL M20C 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. M20C Serial No. EMPTY WEIGHT ARM MOMENT 1000 USE FUL LOAD DATE AND SOURCE OF INFORMATION REVISED 10/78 3-1 MOONEY CORPORATION Engineering Flight Test WEIGHT AND BALANCE MODEL LOADED AS FOLLOWS SERIAL NUMBER DATE REFERENCE (F) - Weight Right Main Wheel = lbs. (F1) - Weight Left Main Wheel = (Fn) - Weight Nose Wheel || || lbs. lbs. (Ft) Total Weight of Aircraft LBS (b) (a) Distance Nose Wheel C to Main Wheel C Distance Reference to Main Wheel C - = inches inches (c) C. G. Location (F)(a) (Ft) )( ( ) inches from main wheels (d) Fuselage Station of Reference Fuselage Station of C. G. = (b) - (c) + (d) inches || inches % MAC