BELL 206L-1 LONG RANGER II PERFORMANCE AND OPERATIONS HANDBOOK

CASA BELL 206L-1 Extract V2.1 Page - 9 SECTION 5 PERFORMANCE DATA The Bell 206L-1 Long Ranger II performance data are contained in this section. The data listed on the graphs are derived from actual flight tests and are intended to provide information to be used in conducting flight operations. POWER CHECK PROCEDURES The Power Check Chart indicates the minimum percent torque that must be available from an engine meeting the minimum Allison specification. The engine must develop these values in order to meet the performance data contained in this flight manual. The takeoff power limits of the 250-C30F engine are: Maximum Torque - 100% (5 minutes). Maximum TOT (turbine outlet temperature) - 791°C (5 minutes) Maximum gas producer RPM (NI) - 104% To perform a Power Check, ensure that the PARTICLE SEP PRG switch is OFF and anti-ice is OFF. Adjust power until helicopter is stabilized in level flight at the maximum airspeed attainable within engine and airframe limits. EXAMPLE: Record the following information from cockpit instruments: Outside Air Temperature - °C Example 18°C Turbine Outlet Temperature - °C Example 740°C Pressure Altitude - Ft. Example 4000 ft. Percent Torque - % (Take your actual reading) Enter Power Check Chart at observed OAT (Example 18°C), proceed vertically to intersection of TOT (Example 740°C) and follow horizontally to intersection with pressure altitude (Example 4000 ft), drop vertically to read chart percent torque (85%). If actual reading of percent torque is the same or greater than the chart percent torque, engine power equals or exceeds minimum performance specification and performance data contained in this manual can be achieved. If actual reading of percent torque is less than chart percent torque, engine power is less than minimum performance specification and all performance data contained in this manual cannot be achieved. Refer to the appropriate maintenance manual to determine cause of low power. 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 10 RATE OF CLIMB Rate of Climb Charts are presented for various combinations of power setting, and anti-ice and particle separator purge switch positions. The rate of climb data shown in the graphs are termed `TAPELINE RATE OF CLIMB', which means actual rate of climb. The rate of climb measured with an altimeter will show tapeline rates of climb only on a standard day, with a standard temperature lapse rate. The following example is for use with rate of Climb - Maximum with Takeoff Power. The example is typical for use with all other Rate of Climb Charts. EXAMPLE: Assume an ambient OAT of 10°C, a pressure altitude of 12,000 feet and a gross weight of 3600 lbs. (1632.9 kilograms) and anti-ice and particle separator purge switches - OFF Enter temperature scale at 10°C, proceed vertically to intersection of the 12,000 feet pressure altitude curve; from this point move horizontally to the right to intersect the 3600 lb. (1632.9 Kg) gross weight line. Drop vertically and read a rate of clime of 1070 feet per minute. RATE OF CLIMB - DOOR(S) OFF Reduce Rate of Climb Chart data 100 feet per minute when operating with any combination of door(s) OFF. BEST RATE OF CLIMB Best Rate of Climb is: CAS IAS 60 MPH 66 MPH 52 kts 57 kts 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 11 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 12 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 13 OPERATION IN ALLOWABLE RELATIVE WIND Satisfactory stability and control has been demonstrated in relative winds of 20 MPH (17 knots) sideward and rearward at all loading conditions within Area A of Hover Ceiling Charts. IGE AND OGE HOVER CEILING CHARTS The IGE and OGE Hover Ceiling Charts present hover performance (allowable gross weight) for various anti-ice and particle separator purge switch positions for conditions of pressure altitude and OAT. Each chart is divided into two areas. AREA A (White Area) as shown on the hover ceiling charts present hover performance for which controllability has been demonstrated in all relative wind conditions up to 20 MPH (17 knots). NOTE Engine TOT will rise noticeably when hovering downwind. Avoid hovering downwind when operating near TOT limits. AREA B (Shaded area) as shown on hover ceiling charts present additional hover performance which can be realized in CALM WINDS or winds outside the CRITICAL RELATIVE WIND AZIMUTH AREA. 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 14 CRITICAL RELATIVE WIND AZIMUTH AREA NOTE Tail rotor control margin and/or control of engine temperature (TOT) may preclude operation in AREA B of the Hover Ceiling Charts when the relative wind is in the Critical Wind Azimuth Area. 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 15 HOVER CEILING The following example is for use with the Hover Ceiling in-ground-effect, takeoff power, anti-ice OFF, particle separator purge - OFF chart and is typical for use of all other Hover Ceiling Charts. EXAMPLE What gross weight hover capability could be expected at a site having the following conditions: Pressure Altitude = 10,000 ft. Outside Air Temperature = 20°C For the above example the pilot must refer to the 0°C to 46°C Hover Ceiling Charts. From the appropriate IGE Chart obtain: A maximum of 3430 pounds (1555.5 kilograms) for all allowable wind conditions, and a maximum of 3900 pounds (1768.7 kilograms) when wind conditions are calm or outside the critical wind azimuth area. From the appropriate OGE Chart obtain: A maximum of 3300 pounds (1496.6 kilograms) for all allowable wind conditions. Notice that for this example the helicopter reaches an engine limit (20°C) and a controllability limit (Area B) at the same gross weight. NOTE The In-Ground-Effect (IGE) and Out-Of-Ground-Effect (OGE) Hover Ceiling Charts are presented separately for the temperatures from 0°C to 46°C and for temperatures from 0°C to -25°C, only for clarity of presentation. 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 16 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 17 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 18 ALTITUDE VS GROSS WEIGHT LIMIT FOR HEIGHT-VELOCITY DIAGRAM 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 19 HEIGHT VELOCITY DIAGRAM The Height-Velocity Diagram defines the conditions from which a safe landing can be made on a smooth, level, firm surface following an engine failure. The Height-Velocity Diagram is valid only when the helicopter gross weight does not exceed the limits of the Altitude Versus Gross Weight Limit for Height-Velocity Diagram. 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 20 SERVICE CEILING 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 21 LONG RANGE CRUISE 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 22 LONG RANGE CRUISE 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 23 SECTION 6 WEIGHT AND BALANCE DATA WEIGHT EMPTY CENTRE OF GRAVITY The empty weight consists of the basic helicopter with required equipment, optional equipment kits, transmission and gearbox oils, hydraulic fluid, unuseable fuel, undrainable engine oil, and fixed ballast. The empty weight centre of gravity shall be adjusted within the limits of the applicable Weight Empty Centre of Gravity chart. GROSS WEIGHT CENTRE OF GRAVITY It shall be the pilots responsibility to ensure that the helicopter is properly loaded so that the entire flight is conducted within the limits of the Gross Weight Centre of Gravity chart in Section 1. The gross weight centre of gravity may be calculated from the helicopter Actual Weight Record (historical records) and the Loading Tables in this section or in appropriate Flight Manual Supplements to assure safe loading. COCKPIT AND CABIN LOADING A minimum crew weight of 170 pounds (77.1 kilograms) in the cockpit is required. Passengers may be loaded in any sequence if only one crew seat is occupied. If both crew seats are occupied, only one mid passenger is permitted unless there are two aft passengers. If any doors are removed gross weight CG shall be computed. The passenger compartment loading limit is 75 pounds per square foot. FUEL LOADING At the beginning of any flight with full fuel on board, the CG of the fuel moves forward as it is consumed. This occurs because fuel is consumed from the aft fuel cell first. The maximum forward CG condition of the fuel occurs when 62.5 gallons (236.6 litres / 192.8 kg) remain. The CG then begins to move aft as the fuel is consumed from the forward fuel cells. The maximum aft CG condition of the fuel occurs when 39.8 gallons (150.6 litres / 122.7 kg) remain. The CG then begins to move forward again as the remaining fuel is consumed. With normal crew and passenger loading, gross weight CG should remain within limits at any fuel quantity. BAGGAGE COMPARTMENT LOADING The baggage compartment is accessible from the left side of the fuselage and contains approximately 16 cubic feet of space. The baggage compartment has a load limit of 250 pounds (113.4 kg) at 86 pounds per square foot. This is a structural limit only and does not infer that the CG will remain within approved limits. When weight is loaded into the baggage compartment, 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 24 indiscriminate crew, passenger and fuel loading can no longer be assumed and the pilot must compute gross weight CG to assure loading within approved limits. Loading of the baggage compartment should be from front to rear. The load shall be secured to tiedown fittings if shifting of the load in flight could result in structural damage to the baggage compartment or in gross weight centre of gravity limits being exceeded. The centre of gravity shall be computed with the load in the most adverse position. WEIGHT AND BALANCE DIAGRAMS AND LOADING TABLES HELICOPTER STATIONS DIAGRAM Several significant helicopter stations are shown. CENTRE OF GRAVITY VS. WEIGHT EMPTY CHART Refer to Maintenance Manual. FUEL LOADING TABLES Fuel loading tables are provided for commercial jet fuels ASTM Type Jet B (JP-4) and types A and A-1 (JP-5). Fuel quantities are listed, with their moments, in 5-gallon increments from 5 gallons through to 98.4 gallons, which is total fuel capacity. CABIN AND BAGGAGE COMPARTMENT TABLE OF MOMENTS This table provides the weight and moment for each passenger station location. The chart also contains a moments column for litter patient(s) and baggage compartment. Weights and their moments are listed in 10-pound increments starting with 40 pounds and ending at 350 pounds. To find moments for weights in excess of 350 pounds, calculate the weight in excess of 350 pounds. Add the appropriate moment for the excess weight to the moment for 350 pounds. This will give the desired moment for the total weight. EXAMPLE: Find the moment for a 450 pound load in the aft seat SOLUTION: 450 pounds - 350 pounds = 100 pounds WEIGHT MOMENT 350 lbs 45150 +100 lbs 12900 TOTAL WEIGHT TOTAL MOMENT 450 LBS 58050 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 25 STATIONS DIAGRAM 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 26 SAMPLE LOADING PROBLEM (ENGLISH UNITS) A helicopter is chartered to transport 4 passengers plus pilot and 200 pounds of baggage for a trip that will require approximately 83 gallons of Jet A or A-1 (JP-5) fuel. The 200 pound pilot will return alone. Determine gross weights and extreme CG conditions for both trips. OUTBOUND FLIGHT ITEM WEIGHT (lbs.) ARM / CG (INCHES) MOMENT Weight Empty 2250 130.8 294300 +Oil 13 205 2665 +Pilot 200 65 13000 +Forward Passenger 200 65 13000 +(1) mid Passenger 180 91 16380 +(2) Aft Passengers 320 129 41280 +Baggage 200 174 34800 Zero Fuel 3363 415425 +Fuel (JP-5) To Full 669.1 130.4 87251 Takeoff CG 4032.1 124.7 502676 -Fuel to most Fwd Fuel -244.1 -35911 Most Forward CG 3788 123.2 466765 -Fuel to most Aft Fuel -154.4 -13375 Most Aft CG 3633.6 124.8 453390 -Fuel to landing -168.6 -24052 Landing CG 3465 123.9 429338 RETURN FLIGHT ITEM WEIGHT (lbs.) ARM / CG (INCHES) MOMENT Weight Empty 2250 130.8 294300 +Oil 13 205 2665 +Pilot 200 65 13000 Zero Fuel 2463 309965 +Fuel (JP-5) To Full 669.1 87251 Takeoff CG 3132.1 126.8 397216 -Fuel to most Fwd Fuel -244.1 -35911 Most Forward CG 2888 125.1 361305 -Fuel to most Aft Fuel -154.4 -13375 Most Aft CG 2733.6 127.3 347930 -Fuel to landing -168.6 -24052 Landing CG 2565 126.3 323878 A check of the takeoff, landing, and critical CG conditions against the Centre of Gravity VS Gross Weight chart in section 1 verified that the entire operation can be conducted within approved limits. 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 27 SAMPLE LOADING PROBLEM (METRIC UNITS) A helicopter is chartered to transport 4 passengers plus pilot and 90.7 kg of baggage for a trip that will require approximately 312 litres of Jet A or A-1 (JP-5) fuel. The 90.7 kg pilot will return alone. Determine gross weight and extreme CG conditions for both trips. OUTBOUND FLIGHT ITEM WEIGHT (kg.) ARM / CG (mm) MOMENT/100 Weight Empty 1020.6 3322.3 33907.4 +Oil 5.9 5207.0 307.2 +Pilot 90.7 1651.0 1497.5 +Forward Passenger 90.7 1651.0 1497.5 +(1) mid Passenger 81.6 2311.4 1886.1 +(2) Aft Passengers 145.1 3276.6 4754.3 +Baggage 90.7 4419.6 4008.6 Zero Fuel 1525.3 47858.6 +Fuel (JP-5) To Full 303.5 10051.9 Takeoff CG 1828.8 3166.6 57910.5 -Fuel to most Fwd Fuel -110.7 -4136.8 Most Forward CG 1718.1 3129.8 53773.7 -Fuel to most Aft Fuel -70.1 -1542.1 Most Aft CG 164.8 3169.4 52231.6 -Fuel to landing -73.8 -2677.6 Landing CG 1574.2 3147.9 49554 RETURN FLIGHT ITEM WEIGHT (kg) ARM / CG (mm) MOMENT/100 Weight Empty 1020.6 3322.3 33907.4 +Oil 5.9 5207.0 307.2 +Pilot 90.7 1651.0 1497.5 Zero Fuel 1117.2 35712.1 +Fuel (JP-5) To Full 303.5 10051.9 Takeoff CG 1420.7 3221.2 45764.0 -Fuel to most Fwd Fuel -110.7 -4136.8 Most Forward CG 1310 3177.6 41627.2 -Fuel to most Aft Fuel -70.1 -1542.1 Most Aft CG 1239.9 3232.9 40085.1 -Fuel to landing -73.8 -2677.6 Landing CG 1166.1 3207.9 37407.5 A check of the takeoff, landing, and critical CG conditions against the Centre of Gravity VS Gross Weight chart in section 1 verified that the entire operation can be conducted within approved limits. 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 28 RECORD OF WEIGHT ALTERATIONS BELL HELICOPTER AUSTRALIA (W/O 3772) AIRCRAFT VH- TYPE BELL 206L-1 DATUM B/L_ ‘0’ C/L of helicopter REWEIGH AIRCRAFT ON OR BEFORE ________ TBA _____________ AIRCRAFT TYPE MAXIMUM GROSS WEIGHT _________ (INTERNAL) 1837.0 kg _________ (EXTERNAL) 1927.8 kg THIS AIRCRAFT AS WEIGHED EMPTY WEIGHT 1020.6 kg AS WEIGHED EMPTY LONGITUDINAL ARM 3322.3 mm AS WEIGHED EMPTY LONGITUDINAL MOMENT /100 33907.4 kg/mm MANUFACTURER'S LONGITUDINAL LIMITS Refer to Gross Weight Centre of Gravity chart, Section 1, Flight Manual, for longitudinal limits. MANUFACTURER'S LATERAL LIMITS Lateral limit is 102mm left of fuselage centre line and 89mm right of fuselage centre line. CONFIGURATION AT TIME OF WEIGHING Empty weight includes litter provisions, cargo hook, 2 x portable fire extinguishers, 2 x first aid kits. 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 29 FUEL LOADING TABLE ASTM TYPE JET A AND A-I (JP-50) U.S. GALLONS Gal. Weight 6.8 lbs/gal CG (in) Moment (in-lbs) Gal. Weight 6.8 lbs/gal CG (in) Moment (in-lbs) ~ ~ ~ ~ 0 0 0 0 60 408.0 122.8 50102 5 34.0 131.5 4471 **62.5 425.0 120.8 51340 10 68.0 135.5 9214 65 442.0 121.7 53791 15 102.0 136.4 13913 70 476.0 123.6 58834 20 136.0 137.0 18632 75 510.0 125.2 63852 25 170.0 137.4 23358 80 544.0 126.7 68925 30 204.0 138.1 28172 85 578.0 127.9 73926 *39.8 270.6 140.3 37965 90 612.0 129.0 78948 45 306.0 135.7 41524 95 646.0 129.8 83851 50 340.0 131.4 44676 98.4 669.1 130.4 87251 55 374.0 127.2 47573 LITERS Litres Weight (Kg) 0.81 Kg/Lit CG (mm) Moment (mm-Kg)/100 Litres Weight (Kg) 0.81 Kg/Lit CG (mm) Moment (mm-Kg)/100 0 0 0 0 210 171.2 3216 5505.8 15 12.2 3282 400.4 225 183.4 3129 5738.6 30 24.5 3426 839.4 **236.6 192.8 3068 5915.1 45 36.7 3452 1266.9 240 195.6 3078 6020.6 60 48.9 3467 1695.4 255 207.8 3119 6481.3 75 61.1 3480 2126.3 270 220.0 3155 6941.0 90 73.4 3487 2559.5 285 232.3 3183 7394.1 105 85.6 3500 2996.0 300 244.5 3213 7855.8 120 97.8 3518 3440.6 315 256.7 3241 8319.6 135 110.0 3541 3895.1 330 269.0 3261 8772.1 *150.6 122.7 3564 4373.0 345 281.2 3282 9229.0 165 134.5 3470 4667.2 360 293.4 3299 9679.3 180 146.7 3381 4959.9 372.4 303.5 3312 10051.9 195 158.9 3302 5246.9 * Critical Fuel for Most AFT CG condition ** Critical Fuel for Most FWD CG condition OIL For CG calculations use the following standard data WT CG MOMENT English units 13 LBS 205 1N. 2665 IN LBS Metric units 5.9 KGS 5207.0 MM 307 MM KGS / 100 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 30 CABIN BAGGAGE COMPARTMENT TABLE OF MOMENTS POUNDS Weight (Pounds) Front Seat F.S. 65 Mid-Pass (Facing Aft) F.S. 91 Aft-Pass (Facing Fwd.) F.S. 129 Litter Patient(s) F.S. 108 Baggage F.S. 174 40 2600 3640 5160 4320 6960 50 3250 4550 6450 5400 8700 60 3900 5460 7740 6480 10440 70 4550 6370 9030 7560 12180 80 5200 7280 10320 8640 13920 90 5850 8190 11610 9720 15660 100 6500 9100 12900 10800 17400 110 7150 10010 14190 11880 19140 120 7800 10920 15480 12960 20880 130 8450 11830 16770 14040 22620 140 9100 12740 18060 15120 24360 150 9750 13650 19350 16200 26100 160 10400 14560 20640 17280 27840 170 11050 15470 21930 18360 29580 180 11700 16380 23220 19440 31320 190 12350 17290 24510 20520 33060 200 13000 18200 25800 21600 34800 210 13650 19110 27090 22680 36540 220 14300 20020 28380 23760 38280 230 14950 20930 29670 24840 40020 240 15600 21840 30960 25920 41760 250 16250 22750 32250 27000 43500 260 16900 23660 33540 28080 270 17550 24570 34830 29160 280 18200 25480 36120 30240 290 18850 26390 37410 31320 300 19500 27300 38700 32400 310 20150 28210 39990 33480 320 20800 29120 41280 34560 330 21450 30030 42570 35640 340 22100 30940 43860 36720 350 22750 31850 45150 37800 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 31 CABIN BAGGAGE COMPARTMENTS TABLE OF MOMENTS MM - Kg 100 KILOGRAMS Weight (Kg) Front Seat F.S. 1651.0 mm Mid-Pass (Facing Aft) F.S. 2311.4 mm Aft-Pass (Facing Fwd.) F.S. 3276.6 mm Litter Patient(s) F.S. 2743.2 mm Baggage F.S. 4419.6 mm 18.1 298.8 418.4 593.1 496.5 800.0 22.7 374.8 524.7 743.8 622.7 1003.2 27.2 449.1 628.7 891.2 746.2 1202.1 31.8 525.0 735.0 1042.0 872.3 1405.4 36.3 599.3 839.0 1189.4 995.8 1604.3 40.8 673.6 943.1 1336.9 1119.2 1803.2 45.4 749.6 1049.4 1487.6 1245.4 2006.5 49.9 823.8 1153.4 1635.0 1368.9 2205.4 54.4 898.1 1257.4 1782.5 1492.3 2404.3 59.0 974.1 1363.7 1933.2 1618.5 2608.6 63.5 1048.4 1467.7 2080.6 1741.9 2806.4 68.0 1122.7 1571.8 2228.1 1865.4 3005.3 72.6 1198.6 1678.1 2378.8 1991.6 3208.6 77.1 1272.9 1782.1 2526.3 2115.0 3407.5 81.6 1347.2 1886.1 2673.7 2238.5 3606.4 86.2 1423.2 1992.4 2824.4 2364.6 3809.7 90.7 1497.5 2096.4 2971.9 2488.1 4008.6 95.3 1573.4 2202.8 3122.6 2614.3 4211.9 99.8 1647.7 2306.8 3270.1 2737.7 4410.8 104.3 1722.0 2410.8 3417.5 2861.2 4609.6 108.9 1797.9 2517.1 3568.2 2987.3 4812.9 113.4 1872.2 2621.1 3715.7 3110.8 5011.8 117.9 1946.5 2725.1 3863.1 3234.2 122.5 2022.5 2831.5 4013.8 3360.4 127.0 2096.8 2935.5 4161.3 3483.9 131.5 2171.1 3039.5 4308.7 3607.3 136.1 2247.0 3145.8 4459.5 3733.5 140.6 2321.3 3249.8 4606.9 3856.9 145.1 2395.6 3353.8 4754.3 3980.4 149.7 2471.5 3460.2 4905.1 4106.6 154.2 2545.8 3564.2 5052.5 4230.0 158.8 2621.8 3670.5 5203.2 4356.2 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 32 SECTION 8 FUEL AND OIL FUEL Fuels conforming to the following commercial and military specifications are approved: ASTM D-1655, Type A, A-1, or B MIL-T-5624, Grade JP-4 or JP-5 NATO F-40 or F-44 Refer to Fuel Limitations in Section 1 The following fuel listing is provided for the convenience of the operator (table 8-1). It shall be the responsibility of the operator and his fuel supplier to ensure that the fuel used in the helicopter conforms to one of the approved specifications above. Refer to Allison Operation and Maintenance Manual for alternate or emergency fuels. FUEL SYSTEM SERVICING Total capacity: 376.3 litres (99.4 U.S. gallons). Useable Fuel: 372.4 litres (98.4 U.S. gallons). The fuel system contains interconnected cells that are serviced through a single fuel port located on the right side of the helicopter. A grounding jack is provided near the fuelling port. An electric sump drain is located in the aft tank and is activated by a button located at the right aft lower side of the fuselage. The battery switch must be ON (or external power applied) and the fuel valve switch must be OFF to activate the sump drain. 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 33 SECTION 9 CHARTS AND TABLES INTRODUCTION The charts and tables contained on the following pages are intended to provide useful information, in this handbook, that normally is located in various and numerous other sources. The prime intent of furnishing this data is to assist in flight planning, operations and, for the purposes other than flight, transposing available information to the type desired. 206L-1 FLIGHT MANUAL CASA BELL 206L-1 Extract V2.1 Page - 34 Density Altitude Chart