SIKORSKY S76 Helicopter Operating Manual

TRANSIENT OPERATION: 52% to 68% N1 - avoid continuous operation in this range 105.35% N1 - 16 second transient power N2 (POWER TURBINE) SPEED LIMITS 114% N2 - maximum at 0% torque varying linearly to 107.1% N2 at 115% torque Transient: 15 second limit varies linearly from 119% at flight autorotation to 109% at 115% torque S76 Performance and Operations Handbook May 2013 10 T5 (POWER TURBINE INLET TEMPERATURE) LIMITS Steady State Limits 885o C - 2-1/2-minute power, one engine inoperative 868o C - Maximum continuous power, one engine inoperative 845o C - Takeoff and maximum continuous, dual-engine Transient Limit 920o C - 16 seconds, single-engine Starting and Shutdown 785o C - No time limitation 785 o C to 865o C - limited to 5 seconds TRANSMISSION LIMITS NOTE Intentional operation above 100% torque, 100% N1, or 8450 C T5 is reserved for actual emergency use only except for required engine maintenance checks described in the engine maintenance manual. TORQUE LIMITS Dual-Engine Operation 100% Torque per engine - Takeoff and maximum continuous NOTE Takeoff torque may exceed 100% on one engine to a maximum of 104% provided that the torque on the other engine is less than 96% and the sum of the individual torque values does not exceed 200%. Single-Engine Operation 111.2% Torque - Maximum continuous power 115.0% Torque - 2-1/2-minute limit 115.0% to 155% Torque - 16 second transient power S76 Performance and Operations Handbook May 2013 11 TRANSMISSION OIL MIL-L21260 Type I, Grade 30 - Low temperature limit -9o C (15o F) Dextron II ATF - Low temperature limit -34o C (-30 o F) TRANSMISSION OIL TEMPERATURE LIMITS Maximum: 120o C (09500 series main gearbox) Minimum: -20o C TRANSMISSION OIL PRESSURE LIMITS Maximum: 120 PSI Minimum: 20 PSI ROTOR LIMITS POWER OFF Maximum: 115% Nr Minimum: 87% Nr Transient: 78% Nr POWER ON Maximum: 107% Nr Minimum: 100% Nr - (dual-engine operation) Minimum: 96% Nr - (one engine inoperative) S76 Performance and Operations Handbook May 2013 12 WEIGHT LIMITS See Figure 1.2.1 for forward and aft centre of gravity limits at various gross weights. Maximum takeoff and landing weight is 10800 pounds (4898 kg). LOADING LIMITS Maximum allowable cabin floor loading is 75 pounds per square foot (366 kg per square metre). Maximum baggage compartment load is 600 pounds (272 kg). CATEGORY "A" OPERATIONS See Figure 1.1.15 for variation of allowable takeoff and landing gross weight with altitude and temperature. CATEGORY "B" OPERATIONS See Figures 1.1.19 to 23 for variation of allowable takeoff and landing gross weight with altitude and temperature. S76 Performance and Operations Handbook May 2013 13 ENGINE OR DRIVE SYSTEM OPERATING LIMITS THIS TABLE IS A SUMMARY OF LIMITATIONS OBSERVE THE FIRST LIMIT ENCOUNTERED FOR ANY GIVEN OPERATING CONDITIONS OPERATING CONDITION TIME TRANSMISSION LIMIT (%) ENGINE TORQUE LIMIT (%) T5°C %N1 %N2 TAKEOFF  100 120.0 845 100 (1) MAXIMUM CONTINUOUS (4)  100 120.0 845 100 (1) 2-1/2 MIN OEI 2-1/2 min 115 146.5 885 101.7 (6) (1) MAXIMUM CONTINUOUS OEI  111.2 126.9 868 101.2 (6) (1) STARTING 5 sec   865 (5)   TRANSIENT OEI 16 sec 155(2) 170.7 (2) 920 104.35 (7)  TRANSIENT 16 sec    105.35  TRANSIENT 15 sec     (3) TRANSIENT 5 sec 115(8) 170.7 (2)    NOTES: (1) 114 % N2 - maximum at 0% torque varying linearly to 107% N2 at 115% torque. (2) Cockpit torque indicator does not read above 120% torque. It has been determined that using the specified usual and emergency procedure, 155% torque will not be exceeded under atmospheric conditions for which operation is approved. (3) 119% N2 at 0% torque varying linearly to 109% N2 at 115.0% torque. (4) See paragraph titled Engine Ratings and Recommended Usage. (5) Time between 785 and 865°C is limited to 5 seconds. (6) N1 values indicated on tachometer in OEI mode. (7) Under twin-engine conditions the indicated N1 is the actual N1 value. If an N1 excursion above 104% is observed while in single-engine flight, note the prevailing OAT and pressure altitude and refer to maintenance manual for action, if any. (8) Dual-engine transient limit - 230% total torque (No.1 torque plus No. 2 torque). Figure 1.1.1 Engine or Drive System Operating Limits S76 Performance and Operations Handbook May 2013 14 Figure 1.1.2 Density Altitude Chart S76 Performance and Operations Handbook May 2013 15 Figure 1.1.3 Temperature Conversion Chart S76 Performance and Operations Handbook May 2013 16 Figure 1.1.4 Airspeed Calibration – Pilot S76 Performance and Operations Handbook May 2013 17 Figure 1.1.5 Airspeed Calibration - Co-pilot S76 Performance and Operations Handbook May 2013 18 Figure 1.1.6 Height Velocity Diagram S76 Performance and Operations Handbook May 2013 19 Figure 1.1.7 Forward Climb Performance Two Engines - Maximum Continuous Power S76 Performance and Operations Handbook May 2013 20 Figure 1.1.8 Forward Climb Performance Two Engines - Normal Cruise Power S76 Performance and Operations Handbook May 2013 21 Figure 1.1.9 Hover Out of Ground Effect Two Engines Operating S76 Performance and Operations Handbook May 2013 22 Figure 1.1.10 Forward Climb Performance OEI - 2½ Minute Power S76 Performance and Operations Handbook May 2013 23 Figure 1.1.11 Forward Climb Performance OEI - Maximum Continuous Power S76 Performance and Operations Handbook May 2013 24 CATEGORY "A" OPERATIONS CATEGORY "A" TAKEOFF DESCRIPTION The Category "A" takeoff procedure shown diagrammatically in Figure 1.1.12 features variable Critical Decision Point (CDP) and Takeoff Safety Speed (V2). The CDP, expressed only in terms of airspeed, is selectable in 1 knot increments between 30 and 45 knots while V2, defined as CDP + 10 knots, varies in 1 knot increments between 40 and 55 knots. This permits payload to be traded off against available field length in such a manner that Category "A" One Engine Inoperative (OEI) climb performance minima can be maintained over a wide range of environmental conditions. Figure 1.1.14 shows the Rejected Takeoff (RTO) and Continued Takeoff (CTO) distances as a function of pressure altitude, temperature, headwind component, CDP speed and V2 speed. RTO and CTO distances are directly proportional to CDP and V2 speeds respectively, therefore lower CDP and V2 speeds equate to shorter field lengths. Figure 1.1.15 shows the maximum takeoff and landing gross weight as a function of pressure altitude, temperature, and CDP/V2 speeds. Maximum takeoff and landing gross weight is also directly proportional to CDP/V2 speeds, therefore higher CDP/V2 speeds can equate to higher maximum takeoff gross weights. The Category "A" takeoff procedure provides the flexibility to address specific payload and/or field length requirements appropriate to either of the following operational scenarios: 1. Determine the maximum takeoff gross weight, given the available field length. 2. Determine the required field length, given the desired mission takeoff gross weight. Specific numerical examples follow which illustrate the use of the charts for each of the above stated scenarios. Example 1 Determine the maximum takeoff gross weight, given the RTO field length, pressure altitude, temperature, and headwind component. 1. Enter Figure 1.1.14 with the RTO space available, and using the headwind component, pressure altitude, and temperature, read the resultant CDP speed. Note: If resultant CDP is greater than 45 knots, use 45 knots as CDP. 2. Enter Figure 1.1.15 with pressure altitude, temperature, and CDP speed from Step 1, and determine the maximum takeoff gross weight. S76 Performance and Operations Handbook May 2013 25 3. Notes: (1) If the horizontal line defined by pressure altitude and temperature intersects 10800 pounds at a CDP speed lower than the CDP from Step 1, use the lower CDP speed, or (2) if the desired takeoff gross weight is less than the maximum permitted takeoff gross weight, use the lower CDP speed corresponding to the desired takeoff gross weight. 4. Using Figure 1.1.14, verify that the CTO distance for V2 (CDP + 10 knots) is suitable for the takeoff area. Given: Available RTO Field Length: 850 ft Pressure Altitude: 3000 ft Temperature: +10 deg C Headwind Component: 20 kt EAPS: Off Determine: CDP Speed: 31 kt Maximum Takeoff Gross Weight: 9400 lb V2 Speed: 41 kt CTO Distance: 1010 ft Example 2 Determine the required field length, given the desired mission takeoff gross weight, pressure altitude, temperature, and headwind component. 1. Enter Figure 1.1.15 for the appropriate EAPS configuration with the desired takeoff gross weight, and using the pressure altitude and temperature, read the resultant CDP and V2 (CDP + 10 kt) speeds. 2. Enter Figure 1.1.14 with pressure altitude and temperature, and using the CDP from Step 1, determine the RTO distance required. 3. For the same values of pressure altitude and temperature as used in Step 2, use V2 (CDP + 10 kt) to determine CTO distance required. Given: Mission Takeoff Gross weight: 10000 lb Pressure Altitude: 3000 ft Temperature: +10 deg C Headwind Component: 20 kt EAPS: OFF S76 Performance and Operations Handbook May 2013 26 Determine: CDP speed: 37 kt V2 speed: 47 kt RTO Distance: 1100 ft CTO Distance: 1200 ft TECHNIQUE Refer to Figure 1.1.12 After determining and setting bugs for CDP and V2 on airspeed indicator, hover at 5-foot wheel height. Increase collective pitch to achieve a 6% torque above hover torque and accelerate forward maintaining 5 to 10 foot wheel height until reaching CDP. After passing CDP rotate nose-up to initiate climb at V2. When clear of obstacles, gradually accelerate to best rate of climb speed (Vy) and retract landing gear. ASSOCIATED CONDITIONS Bleed Air: OFF EAPS/Anti-Ice: OFF or ON S76 Performance and Operations Handbook May 2013 27 Figure 1.1.12 Category "A" - Takeoff Profiles S76 Performance and Operations Handbook May 2013 28 CONDITION: WIND VELOCITY - 40 KT WIND DIRECTION - 130 O FLIGHT PATH - 090 O EXAMPLE: ENTER CHART AT WIND DIRECTION FROM FLIGHT PATH = 40 O MOVE DOWN TO WIND VELOCITY ARC = 40 KT MOVE LEFT TO HEADWIND COMPONENT = 30.6 KT MOVE DOWN TO CROSSWIND COMPONENT = 25.7 KT Figure 1.1.13 Wind Components S76 Performance and Operations Handbook May 2013 29 Figure 1.1.14 Category "A" - Rejected and Continued Takeoff Distance S76 Performance and Operations Handbook May 2013 30 Figure 1.1.15 Category "A" - Maximum Takeoff and Landing Gross Weight S76 Performance and Operations Handbook May 2013 31 CATEGORY "A" LANDING TECHNIQUE Refer to Figure 1.1.16 Establish an approach to arrive at the LDP, a point 200 feet above the touchdown elevation, with 45 KIAS, 107% Nr, and a rate of descent of no more than 600 FPM. Initiate deceleration passing 50 feet at 45 KIAS. Continue approach and deceleration to a running touchdown or hover. Refer to emergency procedures for single-engine landing. ASSOCIATED CONDITIONS Bleed Air: OFF EAPS/Anti-ice: OFF or ON LANDING DISTANCE The landing distances shown in Figure 1.1.18 reflect the one-engine inoperative landings to a hard surfaced runway. Example Determine landing distance required, given pressure altitude, temperature, and headwind component. 1. Enter Figure 1.1.18 at 4000 feet pressure altitude, and using the temperature and headwind component (Figure 1.1.13), read the resultant landing distance required. Given: Pressure Altitude: 4000 ft Temperature: +10 deg C Headwind Component: 10 kt EAPS: OFF Determine: Landing Distance Required: 750 ft S76 Performance and Operations Handbook May 2013 32 Figure 1.1.16 Category "A" - Landing Profile S76 Performance and Operations Handbook May 2013 33 ALTERNATE CATEGORY "A" LANDING TECHNIQUE Refer to Figure 1.1.17 Establish an approach to arrive at the LDP, a point 75 feet above the touchdown elevation, with 60 KIAS, 107% Nr, and a rate of descent of no more than 300 FPM. Upon passing the LDP, initiate a smooth deceleration with collective to continue descent through 50 feet with up to 20 to 25 degree flare attitude. Apply collective to reduce descent rate and decrease flare attitude to pass 20 feet at approximately 30 KIAS. Continue approach and deceleration to a running touchdown or hover. Refer to emergency procedures for single engine landing. ASSOCIATED CONDITIONS Bleed Air: OFF EAPS/Anti-ice: OFF or ON LANDING DISTANCE The landing distance reflects the one engine inoperative landings to a hard surfaced runway. The landing distance is 1000 feet for all weight, altitude, and temperature combinations. S76 Performance and Operations Handbook May 2013 34 Figure 1.1.17 Category "A" - Alternate Landing Profile S76 Performance and Operations Handbook May 2013 35 Figure 1.1.18 Category "A" - Landing Distance from 50 ft Height to Stop S76 Performance and Operations Handbook May 2013 36 CATEGORY "B" OPERATIONS CATEGORY "B" TAKEOFF TECHNIQUE Rise vertically to 5 foot wheel height. Increase collective pitch to achieve up to 10% torque above hover torque (not to exceed takeoff power limits) and accelerate forward maintaining 5 to 10 foot wheel height. Rotate nose-up at 50 KIAS, and climb at 55 KIAS until obstructions are cleared. ASSOCIATED CONDITIONS Bleed Air: OFF EAPS/Anti-ice: OFF or ON TAKEOFF DISTANCE The takeoff distances from 5 foot hover to 50 foot hover height are shown in Figures 1.1.20 to 1.1.23. Example Determine the take off distance required, given temperature, pressure altitude, and mission takeoff gross weight. 1. Enter table for appropriate EAPS configuration with the desired takeoff gross weight, and using temperature and pressure altitude, read takeoff distance required. Given: Mission Takeoff Gross Weight: 9000 lb Temperature: +20 deg C Pressure Altitude: 5000 ft EAPS: OFF Determine: Takeoff Distance: 1100 ft S76 Performance and Operations Handbook May 2013 37 Figure 1.1.19 Category "B" - Maximum Takeoff and Landing Gross Weight S76 Performance and Operations Handbook May 2013 38 Figure 1.1.20 Category "B" - Takeoff Distance (Sheet 1 of 4) S76 Performance and Operations Handbook May 2013 39 Figure 1.1.21 Category "B" - Takeoff Distance (Sheet 2 of 4) S76 Performance and Operations Handbook May 2013 40 Figure 1.1.22 Category "B" - Takeoff Distance (Sheet 3 of 4)