Performance Data for the Robinson R22 Beta

DEMONSTRATED CONDITIONS: SMOOTH HARD SURFACE WIND CALM 103-104 % RPM AVOID OPERATION IN SHADED AREAS 10 700 650 600 550 500 450 400 350 300 250 200 150 100 50 50 7000 ft DENSITY ALTITUDE at 1300 lb SEA LEVEL at 1370 lb RECOMMENDED TAKEOFF PROFILE 0 10 20 30 40 50 60 70 80 90 100 KIAS HEIGHT - VELOCITY DIAGRAM FAA APPROVED: 13 OCT 2000 5-10 ROBINSON MODEL R22 SECTION 6 WEIGHT AND BALANCE HELICOPTER WEIGHING PROCEDURES (cont'd) 8. Raise aircraft and place 500 lb. capacity weight scales under each skid. Locate center of scales 10 inches for- ward of aft end of skids. 9. Lower aircraft until it rests entirely on scales. Aircraft must be well balanced on scales before releasing tail. Be sure aircraft is level laterally by placing level on center of aft landing gear crosstube. 10. Record empty weight. R Scale lb L Scale lb Tare lb Empty weight: lb BASIC EMPTY WEIGHT & C.G. ITEM Weight (lb) C.G. Arm** Moment* (in.) (lb-in.) Ship as weighed (from 7 & 10) Add drained unusable fuel 0.6 108.6 65 Helicopter Basic Empty Weight (Includes unusable fuel & full oil) *Moment = Weight x C.G. Arm **Arm measured from Datum located 100 inches forward of rotor centerline. ISSUED: 12 OCTOBER 1983 6-3 ROBINSON MODEL R22 SECTION 6 WEIGHT AND BALANCE LATERAL CG POSITION It is usually not necessary to determine the lateral CG position as most optional equipment is located near the helicopter centerline. However, if an unusual installation or loading oc- curs which could affect the lateral CG, its position should be checked against the CG envelope contained in Section 2. The lateral CG position can be calculated by multiplying the weights of all items, not symmetrical about the centerline, times their arm from the centerline. Then considering all items on the right as positive and those on the left as negative, sum the moments and divide the total by the weight of the loaded helicopter. This will give you the lateral position which, together with the CG position aft of the datum, can be com- pared with the allowable CG envelope in Section 2. When weighing the helicopter, the center distance between the skids must be accurately measured while the ship is resting on the scales. The lateral CG position equals: (R scale reading L scale reading) × 12 Distance between skids (R scale reading + L scale reading). The following CG locations may be used when determining the helicopter CG position. Item Pilot & Baggage under R seat Passenger & Baggage under L seat Main Fuel Aux Fuel (optional) *See note on Page 6-7 REVISED: 15 SEPTEMBER 1987 Long CG Lat CG *79.0 + 10.7 *79.0 - 9.3 108.6 - 11.0 103.8 + 11.2 6-6 ROBINSON MODEL R22 LOADING INSTRUCTIONS SECTION 6 WEIGHT AND BALANCE The following sample loading calculation may be used to determine the total moment of your helicopter. Both the mo- ment with take-off fuel and the moment with empty fuel must be within the allowable moment shown on the diagram. SAMPLE LOADING CALCULATION Arm Inches from Datum Sample Helicopter Your Helicopter Weight Moment Weight Moment (lbs) (lb-in) (lbs) (lb-in) 1. Basic Empty Weight as Equipped 104.8 830 86,984 (Includes unusable fuel and full oil) 2. Pilot, Passenger and *78.0 425 33,150 Baggage Total Weight and Balance with zero usable fuel 95.7 1255 120,134 3. Usable Fuel at 6 lbs/gal. 108.6 115 12,489 Total Weight & Balance with take-off fuel 96.8 1370 132,623 (Note: The CG location aft of the datum, for the loaded helicopter, can be determined by dividing the total weight into the total moment.) *Use 78.0 for S/N 256 and subsequent and for aircraft equipped with new type seats installed after DEC. 22, 1981. Use 79.0 for aircraft prior to S/N 256 with original seats. If cushion is used, subtract compressed thickness of cushion from arm. REVISED: 15 SEPTEMBER 1987 6-7 LOADED HELICOPTER WEIGHT - LBS. ROBINSON MODEL R22 SECTION 6 WEIGHT AND BALANCE 1300 1200 1100 1000 900 80 90 ALLOWABLE MOMENT 100 110 120 130 140 LOADED HELICOPTER MOMENT - 1000 INCH LBS. R22 STANDARD AND HP ALLOWABLE CG MOMENT VS. GROSS WEIGHT ENVELOPE REVISED: 15 SEPTEMBER 1987 6-8