CRUISE EXAMPLE

EAPS Penalty Table (Continued) - TM-1-1520-240-10_361

Figure 7-7-1 Example Cruise Chart (Sheet 2 of 2)

TM-1-1520-240-10 Army CH-47D Heilcopter (EIC:RCD) Manual
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TM 1-1520-240-10 7-7-6 CRUISE EXAMPLE EXAMPLE 1 (DUAL ENGINE) WANTED: SPEED FOR MAXIMUM ENDURANCE SPEED FOR MAXIMUM RANGE MAX. SPEED AT CONTINUOUS TORQUE RATING ESTIMATED AIRSPEED LIMIT WITH CRUISE GUIDE INDICATOR OPERATIVE KNOWN: GROSS WEIGHT = 50,000 LB. PRESSURE ALTITUDE = SEA LEVEL FAT = 30_C METHOD: READ SPEEDS WHERE GROSS WEIGHT LINE INTERSECTS PERFORMANCE OR LIMIT LINE MAXIMUM ENDURANCE: TAS = 89 KN, IAS = 83 MAXIMUM RANGE: TAS = 144 KN, IAS = 140 KN (REQUIRES POWER IN EXCESS OF MAX CONTINUOUS POWER) MAX SPEED (CONTINUOUS TORQUE RATING): TAS = 130 KN, IAS = 127 KN ESTIMATED AIRSPEED LIMIT (VCGI): 152 KN IAS = 148 KN EXAMPLE 2 (DUAL ENGINE) (DASH LINE) WANTED: TORQUE REQUIRED FOR LEVEL FLIGHT, FUEL FLOW, AND INDICATED AIRSPEED AT TAS = 120 KN. KNOWN: GROSS WEIGHT = 45,000 LB. PRESSURE ALTITUDE = SEA LEVEL FAT = 35_C TRUE AIRSPEED = 120KN METHOD 1 (SIMPLEST) USE NEXT HIGHER TEMPERATURE (40_C) ENTER TAS, MOVE RIGHT TO GROSS WEIGHT MOVE DOWN READ TORQUE REQ’D = 55% (PER ENGINE 0 MOVE UP READ FUEL FLOW = 2670 LB/HR (TOTAL) MOVE RIGHT READ IAS = 114 KN METHOD 2 (INTERPOLATE) READ TORQUE REQ’D, FUEL FLOW, AND IAS AT EACH ADJACENT TEMPERATURE THEN INTER- POLATE BETWEEN TEMPERATURES (REFER TO TABLE BELOW) PRESSURE ALTITUDE SEA LEVEL SEA LEVEL SEA LEVEL FAT 30_C 40_C 35_C TORQUE REQ’D (%) 54.7% 55% 54.9% FUEL FLOW (LB/HR) 2620 2670 2645 IAS (KNOTS) 117 114 115.5 Figure 7-7-1. Example Cruise Chart (Sheet 1 of 2)

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