Flight Manual - Sections 5 & 6 Performance Charts and Weight & Balance EC 130 B4 Initial Pilot Ground School Flight Manual - Sections 5 & 6 Performance Charts and Weight & Balance

Chapter 16 - Performance Charts and Weight & Balance Height - Velocity Diagram ……… ..………………………………. 16.3 & 16.4 Engine Power Check Chart …………………………………….…. 16.5 & 16.6 T4 Check Chart ………………………………………………………………. 16.7 Hover In Ground Effect Chart ……………………………………………. 16.8 Hover Out of Ground Effect Chart ………………………………. 16.9 & 16.10 Arriel Cycle Counting ...…………………………………………………… 16.11 Weight and Balance Section ………………………………………………. 16.12 Basic Datum Planes ………………………………………………………… 16.17 Weight and Balance Arms ……...…………………………………………. 16.18 Longitudinal Center of Gravity Calculation ………………….………… 16.19 Longitudinal Center of Gravity Chart ……………………………………. 16.20 Lateral Center of Gravity Calculation ……………...………….………… 16.21 Lateral Center of Gravity Chart …………………………...………………. 16.22 16.2

Height / Velocity Diagram The Avoidance Zone is defined by five points: Constant Points Point A - Constant at 7 feet AGL skid height and 0 knots airspeed (low hover point) Point B - Constant at 30 feet AGL skid height and 50 knots airspeed Point C - Constant at 100 feet AGL skid height and 65 knots airspeed Variable Points Point D - Variable height (700 ft < height < 1000 ft) depending on the altitude & on the aircraft weight as determined by line (D), and a constant airspeed of 20 knots. Point E - Variable height (700 ft < height < 1000 ft) depending on the altitude and on the aircraft weight as determined by line (D), and a constant zero airspeed. Working the Chart Plot OAT, then go vertical to pressure altitude reference line Horizontal from Hp to aircraft weight, then vertical down to “D” reference line Horizontal from “D” reference line to 0 airspeed line on chart. This is point “E” Continue horizontally to the 20 knot reference line. This is point “D” Connect the points A, B, C, D, and E to obtain the Height - Velocity Envelope Flight Manual - Section 5 - Page 5 - 6 16.3

EC130 B4 OAT = 50 C Hp = 4000’ Weight = 2400 kg Line (D) = 850’ AVOID! Reference Line “D” 20 kt C A B Flight Manual - Section 5 - Page 5 - 7 16.4

Engine Power Check Procedure Before Takeoff In HIGE at 5 ft and before initiating forward flight, pull the collective pitch lever slightly to ensure that the Ng can increase by at least 1%. In-Flight Perform a VEMD engine check (Hp less than 12,000 ft and heating and demisting OFF [ and ~ MCP ]). [ The torque margin and T4 checks are performed automatically by the VEMD with the “Engine Power Check” page. The results are displayed and recorded automatically. ] Manual Engine Check In stabilized level flight at the maximum Ng displayed, note the following parameters: Tq, Ng, NR, OAT, and T4. Read the figures ENGINE POWER CHECK and T4 CHECK in the direction indicated by the arrows. Engine power check is OK if point “P” is located in the area marked “CORRECT”. T4 check is OK if point “T” is located in the area marked “CORRECT”. Flight Manual - Section 5 - Pages 5 - 1 16.5

EC130 B4 Tq = 83% NR = 392 rpm Hp = 1000’ OAT = 150 C Ng = 92% 92% P INCORRECT Tq = 83% NR = 392 rpm Hp = 1000’ OAT = 150 C Ng = 92% 92% CORRECT P 100 C Hp 1000’ 392 rpm Tq 83% Flight Manual - Section 5 - Page 5 - 2 16.6

EC130 B4 T4 = 7600 C Hp = 5000’ OAT = 150 C Ng = 93% 7600 T 93% 5000’ INCORRECT CORRECT 7600 T 93% 5000’ 150 Flight Manual - Section 5 - Page 5 - 3 16.7

EC130 B4 Hp = 9500’ OAT = 100 C 9500’ 5182 lb Flight Manual - Section 5 - Page 5 - 8 16.8

EC130 B4 Hp = 7000’ OAT = 200 C The temperature and pressure altitude are known. What is the maximum allowable Gross Weight that you can hover out of ground effect under these conditions? 7000’ 5160 lb Flight Manual - Section 5 - Page 5 - 9 16.9

EC130 B4 Hp = 12,000’ OAT = 300 C Gross Wt. = 5000 lbs. You are required to sling load an air conditioning unit from sea level to the top of a mountain. Upon arrival you will need to hover out of ground effect. Under these conditions can you safely accomplish this mission? 12,000’ 4000 lb Flight Manual - Section 5 - Page 5 - 9 16.10

Arriel Cycle Counting 16.11 Max NG K1 Min NG K2 100 % 1.0 100 % 1.0 99 % 0.9 98 % 0.8 97 % 0.7 96 % 0.65 95 % 0.6 94 % 0.55 93 % 0.5 Min NG K2 85 - 81 % .05 (Normal Appr.) 80 - 76 % .10 75 - 70 % .15 (Autorotations) 16.11

Weight & Balance 16.12

Empty Weight (E.W.) = EW  3130 lbs Vehicle + engine + common equipment + lubricants, hydraulic + unusable fuel Empty Weight (E.W.) = EW  3130 lbs Flight Manual - Section 6 16.13

Equipped Empty Weight (E.E.W.) Equals EW + Specific Mission Equipment Flight Manual - Section 6 16.14

All Up Weight (A.U.W.) = [ Gross Weight ] Equipped Empty Weight (EEW) + crew + payload + usable fuel All Up Weight (A.U.W.) = [ Gross Weight ] A.U.W. max: 5291 lbs Flight Manual - Section 6 16.15

Weight and Balance Calculation Total Moment divided by Weight X Arm = Moment Total Moment divided by Total Weight equals Center of Gravity Flight Manual - Section 6 16.16

Datum Planes Flight Manual - Section 6 16.17

Weight and Balance Arms 133.8” NOTE: 1” = 25.4 mm 1 mm = .039” 51.2” 199.8” 18” 18” Flight Manual - Section 6 16.18

Longitudinal Center of Gravity Calculation CG = moment weight B = 2.415 m (95.08 in) A = 1.55 m (61.02 in) REFERENCE DATUM LINE C = 3.20 m (125.98 in) (SIDE CARGO) Fuel = 3.475 m (136.81 in) D = 4.60 m (181.10 in) (AFT CARGO) Flight Manual - Section 6 16.19

Longitudinal CG 5291 Within CG Maximum permissible weight in flight, for IGE, takeoff & landing 5291 4952 lbs Within CG Minimum permissible weight in flight 127.21 Flight Manual - Limitations Section - Page 2 - 2 16.20

Lateral Center of Gravity Calculation D + E + + - A - B - C - D - E - A = 23.62 in. C = 28.94 in. E = 23.62 in. B = 0.79 in. D = 9.65 in. NOTE The central front seat has a slight offset from the longitudinal axis. - right hand pilot version (basic) : B - = -0.79 inches - left hand pilot version (optional) : B + = +0.79 inches Flight Manual - Section 6 16.21

Flight Manual - Sections 5 & 6 Performance Charts and Weight & Balance EC 130 B4 Initial Pilot Ground School End of Flight Manual - Sections 5 & 6 Performance Charts and Weight & Balance