CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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SECTION V PERFORMANCE DATA 5−1. GENERAL This section contains baseline helicopter performance information as defined within certain conditions such as airspeed, weight, altitude, temperature, wind velocity and engine power available. Data is applicable to the basic helicopter without any optional equipment installed unless otherwise noted.
5−2. NOISE CHARACTERISTICS NOTE: No determination has been made by the Federal Aviation Administration that the noise levels in this manual are or should be acceptable or unacceptable for operation at, into, or out of any airport. Certification Noise Levels The following noise levels comply with FAR Part 36, Appendix J noise re quirements and were obtained by using FAA approved analysis techniques and FAA approved data from actual noise tests. Table 5−1. Model 600N Noise Characteristics Model: MD 600N
Gross Weight: 4100 Lbs
Engine: Rolls−Royce 250−C47M
VH (KTAS) (S.L. @77°F)
Level Flyover SEL (dBA)
133
79.0
Configuration Clean aircraft, doors on, no external kits installed
FAA Approved Revision 13
The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
5−1
CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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5−3. DENSITY ALTITUDE CHART Description: The chart allows a quick estimation of the density altitude when pressure altitude and OAT are known. This chart can also be used to deter mine true airspeed. Use of Chart: To determine density altitude, the pilot must know pressure altitude and outside air temperature. Enter bottom of chart with known or estimated OAT, move up to known pressure altitude line, move to left and note densi ty altitude. Pressure altitude is found by setting 29.92 (1013 mb) in Kolsman win dow ± altimeter error. To determine true airspeed convert indicated airspeed (IAS) to calibrated airspeed (CAS) utilizing the Airspeed Calibration Curve (Ref. Figure 5-2). On Density Altitude Chart read value on right of chart opposite known den sity altitude. Multiply CAS by this value to determine true airspeed. Examples: Find density altitude for 6000 HP at -15°C: Follow -15°C line to 6,000 ft pressure altitude line; read density altitude (3800 ft). Find density factor: Read directly across from density altitude: (3800 ft). Note density factor of 1.058. Find true airspeed: 130 KIAS = 126.5 KCAS (Ref. Figure 5-2.) 126.5 KCAS 1.058 = 133.8; round to 134 knots true airspeed (KTAS).
5−2
FAA Approved The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to Original other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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20000 1.36 1.34 18000
1.32 1.30
16000
1.28 1.26
14000
1.24 1.22
DENSITY ALTITUDE - FEET
12000
1.20 1.18
10000
1.16 1.14
8000 1.12 1.10
6000
1.08 4000
1.06 1.04
2000 1.02 0
1.00 0.98
-2000 -40
-30
-40 -30 -20 -10
-20
-10
0
10
0
20
30
10 20 TEMPERATURE - °C 40 50 60 70 TEMPERATURE - °F
30
80
90
40
100 110
50
120
60
130 140 F60−015
Figure 5−1. Density Altitude Chart FAA Approved Original
The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
5−3
CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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5−4. AIRSPEED CALIBRATION Description: The chart shows the difference between indicated and calibrated airspeeds (Ref. Figure 5-2). Knots indicated airspeed (KIAS) corrected for position error equals knots cali brated airspeed (KCAS). Use of chart: Use the chart as illustrated by the example. To determine cali brated airspeed, the pilot must know the indicated airspeed. Example: Wanted: Calibrated airspeed Known: Indicated airspeed = 120 knots Method: Enter the bottom of the chart at the indicated airspeed of 120 knots. Move up to the airspeed calibration line; move left and read approximately 118 knots, calibrated airspeed.
5−4
FAA Approved The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to Original other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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160
140
CALIBRATED AIRSPEED - KNOTS
120
100
80
60
40
20
0 0
20
40
60
80
100
120
140
160
INDICATED AIRSPEED - KNOTS
F60−016
Figure 5−2. Airspeed Calibration Curve FAA Approved Original
The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
5−5
CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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5−5. BEST RATE OF CLIMB / MINIMUM RATE OF DESCENT SPEED Description: This chart shows the indicated airspeed to use for the best rate of climb at any given density altitude. This chart also provides an airspeed for the minimum rate of descent and maximum glide distance in autorotation, however, the same rates of climb and descent can be obtained for airspeeds as low as 50 KIAS. Use of Chart: Use the chart as illustrated by the example below. Example: Wanted: Speed for best rate of climb (YSAS not installed) Known: Density altitude = 8,000 feet Method: Enter the left side of chart at the known density altitude of 8,000 feet. Move to the right to the best rate of climb speed curve and then directly down to read approximately 78 KIAS as the best rate of climb speed.
5−6
FAA Approved The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to Revision 6 other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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20000
18000
16000
14000
DENSITY ALTITUDE - FEET
12000
10000
8000
6000
4000
2000
0 45
50
55
60
65
70
INDICATED AIRSPEED - KNOTS
75
80
85 F60−017
Figure 5−3. Best Rate of Climb Speed FAA Approved Revision 6
The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
5−7
CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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5−6. HOVER CEILING − IN GROUND EFFECT (IGE) Description: The hover ceiling chart shows the maximum hover weight capability, in ground effect (IGE), at take off power for known conditions of pressure altitude and outside air temperature, or alternately, the maximum hover ceiling for a known gross weight and outside air temperature. Separate hover performance charts are provided for helicopters equipped with either the engine air inlet particle separator or standard engine air inlet screen. For many operations, a reduction in gross weight capability as a result of elec trical load or use of engine bleed devices still allows the aircraft to operate at the maximum gross weight as depicted on the chart. Use of Chart: The following example explains the correct use of the IGE Chart in Figure 5-4. Example: Wanted: Maximum gross weight for hover at 3.5 feet skid height at takeoff power. Known: HP = 10,000 feet; OAT = 10°C, cabin heat ON, anti-ice and scav air OFF; 40 amp electrical load. Method: Enter the left-hand chart at 10°C and move vertically to the 10,000 Ft pressure altitude line. From this point, move directly to the right to the 10°C line (on right-hand chart). From this point, move down to read 3875 lb from the gross weight scale. Because the helicopter in this example has the cabin heat on, we must subtract 128 lb from the 3875 gross weight capability as de termined from the chart, resulting in a gross weight of 3747 lb. If the cabin heat was not on, then the actual hover gross weight would be limited to 3850 lb.
CAUTION
Gross weights above 3850 LB must be external and jettisonable.
NOTE: Critical wind azimuth limitations may apply. Refer to Section II.
5−8
FAA Approved The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to Original other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
FAA Approved Original
-30
-4000
-25
-20
-10 -5
0
5
10
15
20
25
30
35
AMBIENT TEMPERATURE − DEGREES C
-15
40
45
50
55
SL
2000
4000
6000
8000
10000
60 3000
155 128 106
0
3200
3400
3800
4000
4200
−25
GROSS WEIGHT − POUNDS
3600
GROSS WEIGHTS TO RIGHT OF LINE MUST BE EXTERNAL AND JETTISONABLE
ISA + 37C
337 274 223
0
ALL
4400
−15 −5
35
25
4800
4500 LBS MAXIMUM EXTERNAL GROSS WEIGHT
4600
15
45
5
OAT − DEGREES C
NOTE: DASHED LINES ARE PRESENTED TO PROVIDE EXTERNAL LOAD HOVER CAPABILITY INFORMATION ONLY.
58 49 39
0
SCAV AIR CABIN HEAT
TM
-2000
12000
PRESSURE ALTITUDE - FEET
221 179 147
ANTI−ICE 0
[600N RFM Book TOC]
0
2000
4000
6000
8000
14000
4001 TO 8000 8001 TO 12000 12001 TO 16000
PRESSURE ALT FT. SL TO 4000
DECREASE WEIGHT CAPABILITIES AS FOLLOWS. (APPLICABLE TO ALL TEMPERATURES)
[ Main Menu ]
10000
12000
14000
16000
PER 10 AMP DECREASE/INCREASE IN ELECTRICAL LOAD.
INCREASE OR DECREASE WEIGHT 4 LBS (ABOVE CRITICAL ALTITUDE)
40 AMPERES. FOR ELECTRICAL LOADS OTHER THAN 40 AMPS,
PARTICLE SEPARATOR SCAVENGE AIR OFF, ELECTRICAL LOAD
THIS CHART BASED ON CABIN HEAT AND ENGINE ANTI−ICE OFF,
MD 600N ROTORCRAFT FLIGHT MANUAL CSP−600RFM−1
Performance Data
[RFM Sec 5 TOC]
DENSITY ALTITUDE - FEET
F60-018-1B
Figure 5−4. Hover Ceiling, IGE, 3.5 Foot Skid Height, Takeoff Power Extended Landing Gear, Particle Separator Inlet
5−9
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16000
14000
12000
10000
8000
6000
4000
2000
0
-2000
-4000
THIS CHART BASED ON CABIN HEAT AND ENGINE ANTI−ICE OFF, PARTICLE SEPARATOR SCAVENGE AIR OFF, ELECTRICAL LOAD 40 AMPERES. FOR ELECTRICAL LOADS OTHER THAN 40 AMPS, INCREASE OR DECREASE WEIGHT 4 LBS (ABOVE CRITICAL ALTITUDE)
-25
-20
12000
PRESSURE ALTITUDE - FEET 10000
8000
6000
4000
2000
SL
3200
0 122 103 83
ANTI−ICE
0 158 130 107
CABIN HEAT
DECREASE WEIGHT CAPABILITIES AS FOLLOWS. (APPLICABLE TO ALL TEMPERATURES)
3400
3600
BOTH
0 278
230
188
35
4600
45
25
15
4500 LBS MAXIMUM EXTERNAL GROSS WEIGHT
OAT − DEGREES C −5
5
4400
ISA + 37C
4200
−15
−25
4000
GROSS WEIGHT − POUNDS
3800
GROSS WEIGHTS TO RIGHT OF LINE MUST BE EXTERNAL AND JETTISONABLE
NOTE: DASHED LINES ARE PRESENTED TO PROVIDE EXTERNAL LOAD HOVER CAPABILITY INFORMATION ONLY.
SL TO 4000 4001 TO 8000 8001 TO 12000 12001 TO 16000
PRESSURE ALT FT.
-10 0 10 20 30 40 50 60 3000 -15 -5 5 15 25 35 45 55 AMBIENT TEMPERATURE − DEGREES C
14000
PER 10 AMP DECREASE/INCREASE IN ELECTRICAL LOAD.
-30
F60−018−2B
4800
FAA Approved The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to Original other documents or used or disclosed to others for manufacturing or any other
5−10
MD 600N ROTORCRAFT FLIGHT MANUAL CSP−600RFM−1
TM
Performance Data
DENSITY ALTITUDE - FEET
Figure 5−5. Hover Ceiling, IGE, 3.5 Foot Skid Height, Takeoff Power, Extended Landing Gear, Standard Engine Air Inlet
purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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5−7. GLIDE DISTANCE IN AUTOROTATION Description: The glide distance chart allows the pilot to determine the glide distance attainable following an engine failure from a known altitude above ground and at 85 KIAS. Use of Chart: The following example explains the correct use of the Glide Distance Chart. Example: Wanted: Glide distance in nautical miles (NM) Known: Altitude = 6000 FT AGL NR = 90 or 100% Method: Enter the chart at the 6000 FT AGL line and move right to the solid rotor RPM line. Now move directly down to the glide distance scale and read the glide distance of 4 nautical miles. 20000 18000 16000
ALTITUDE (AGL) - FEET
14000 12000 106% NR
10000
90 AND 100% NR 8000 6000 4000 2000 0 0
2
4
6
8
10
GLIDE DISTANCE - NM
12
14 F60−045
Figure 5−6. Glide Distance
FAA Approved Revision 6
The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
5−11
CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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5−8. HEIGHT − VELOCITY ENVELOPE Height-Velocity Diagram (Figure 5-7) Description: Airspeed/altitude combinations to be avoided in the event of an engine failure during takeoff are shown in the height-velocity diagram. The height velocity diagram is based on the following conditions. 1. 7000 HD. 2. 3850 LB gross weight. 3. Winds less than 3 knots. 4. Smooth hard landing surface. Observe the shaded regions of the Height−Velocity Diagram. These
WARNING represent airspeed/altitude combinations from which a successful
autorotation landing would be difficult to perform. Operation within the shaded area is not prohibited, but should be avoided.
Use of Chart: The recommended takeoff profile line shows the airspeed/altitude combina tions recommended for takeoff using not more than 10% above hover power until clear of height-velocity diagram shaded areas.
5−12
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CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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[600N RFM Book TOC] 1000
900
800
ALTITUDE − AGL (FEET)
700
600
500
400
300
200
100
0
ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÌÌÌÌÌÌÌÌÌÌÌÌ ÑÑÑÑÑÑÑÑÑÑÑÑÑ ÌÌÌÌÌÌÌÌÌÌÌÌ ÑÑÑÑÑÑÑÑÑÑÑÑÑ SMOOTH HARD SURFACE WIND CALM AVOID OPERATIONS IN SHADED AREA
RECOMMENDED TAKEOFF PROFILE
0
NOTE: LOW HOVER POINT IS AT 6 FT SKID HEIGHT
25
50
75
100
INDICATED AIRSPEED − KNOTS
125
150
F60−020
Figure 5−7. Height − Velocity Diagram
FAA Approved Original
The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc
5−13
CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
Performance Data
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5−9. POWER ASSURANCE CHECK The Power Check Chart (Ref. Figure 5-8) shows the relationship of engine torque, turbine outlet temperature, and horsepower at various conditions of pressure altitude and OAT for a Rolls-Royce 250-C47M engine producing speci fication power as installed in the Model 600N helicopter with either the stan dard engine air inlet screen or optional particle separator inlet. The primary purpose of this chart is its use as an engine performance trending tool to aid in determining whether the engine is producing specification power, or if engine power deterioration has occurred.
NOTE: Power check data taken at regular intervals should be plotted to monitor trends in engine condition. See Rolls−Royce 250−C47M Series Operation and Maintenance Manual for additional information on trend analysis. The power check chart is based on the following conditions: Aircraft in a stabilized hover Cabin heat and engine anti-ice OFF Particle separator SCAV AIR OFF 40 amperes electrical load Engine bleed valve closed
NOTE: Reset altimeter if required after obtaining pressure altitude.
5−14
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CSP−600RFM−1
MD 600N ROTORCRAFT FLIGHT MANUAL
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Use Of Chart: The primary use of the chart is illustrated by the example below. To deter mine power check values, it is necessary to read and record engine TORQUE PRESSURE, TURBINE OUTLET TEMPERATURE, PRESSURE ALTITUDE, and OAT while the helicopter is in a stabilized hover.
NOTE: The following example assumes a MD 600N with optional particle separator inlet installed. Example: DATA OBTAINED DURING HOVERING: Torque = 400 Q TOT = 640°C PA = 3000 feet OAT = 25°C METHOD: 1. Enter the bottom right of the chart at 400 Q. Move up along the 400 Q line to the 3000 foot pressure altitude curve. Move left to the solid 25°C OAT line; now move down and read specification TOT of approximately 654°C. 2. Compare the specification TOT of 654°C with the TOT observed during flight (640°C for this example). The TOT that was observed is lower than the specification TOT. If the TOT observed had been higher than the speci fication TOT read from the chart, some power deterioration will have oc curred and the performance data given in this manual may not be obtained.
NOTE: When trend check procedures indicate engine power deterioration, refer to the Rolls−Royce Operation and Maintenance Manual for corrective action.
FAA Approved Revision 13
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FAA Approved The information disclosed herein is proprietary to MD Helicopters, Inc. Neither this document nor any part hereof may be reproduced or transferred to Revision 12 other documents or used or disclosed to others for manufacturing or any other purpose except as specifically authorized in writing by MD Helicopters, Inc. Copyright © 1999−2014 by MD Helicopters, Inc