CSP-HE/HS-1
ROTORCRAFT FLIGHT MANUAL
Additional Operations
and Performance Data
MD 500
(Models 369HE/HS/HM
)
Revision 6
8-4
20,000
18,000
14,000
12,000
10,000
8,000
6,000
4,000
2,000
0
16,000
PRESSURE
AL
TITUDE − FEET
PRESSURE
AL
TITUDE − METERS
AMBIENT TEMPERATURE - DEGREES C
−30
−10
0
10
20
30
40
−40
−20
50
6,000
5,000
4,000
3,000
2,000
1,000
0
THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELEC−
TRICAL LOAD 30 AMPERE. 250−C20 ENGINE
REDUCE HOVER WEIGHT CAPABILITY
1. 33 LB WITH SCAVENGE AIR ON
2.. 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED
3. REDUCE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE OVER AND
ABOVE ANY OTHER HOVER REDUCTION FOR ANY OTHER INSTALLED KIT
(OR BASIC AIRCRAFT) WHEN THE PARTICLE SEPARATOR IS INSTALLED.
2
WT LBS
5
7
-5
15
35
INCREASE (OR DECREASE) WEIGHT
CAPABILITY (ABOVE CRITICAL ALTITUDE) PER
10 AMPERE REDUCTION (OR INCREASE) IN
ELECTRICAL LOAD
OAT
°
C
REDUCE WEIGHT CAPABILITY LBS AS FOLLOWS
PRESSURE
CABIN
HEAT
ANTI-
ICE
BOTH
12,000
132
144
288
16,000
20,000
116
98
123
108
250
217
ALT. FT
SEA LEVEL
TO
GROSS WEIGHTS ABOVE 2550 LB
MUST BE EXTERNAL AND JETTI−
SONABLE
F01-069A
*Figure 8-3. Hover Ceiling Vs Temperature, OGE, Utility Floats, Takeoff Power
<<<< Allison 250-C20>>>>
