MD Helicopters MILVIZ MD530F, Rotorcraft Flight Manual, Page: 167 / 326

<<<< Allison 250
−
C18 >>>>
FAA Approved
Revision 5
5
−
25
CSP
−
HE/HS
−
1
Performance Data
MD 500
(Models 369HE/HS/HM) ROTORCRAFT FLIGHT MANUAL
REDUCE WEIGHT CAPABILITY LBS AS FOLLOWS
ALTITUDE
FT
CABIN
HEAT
ANTI
−
ICE
BOTH
SEA LEVEL
TO
5,000
10,000
15,000
20,000
162
125
105
90
204
150
130
110 405
295
255
210
P
R
E
S
S
U
R
E
A
L
T
IT
U
D
E
−
M
E
T
E
R
S
P
R
E
S
S
U
R
E
A
L
T
IT
U
D
E
−
F
E
E
T
20,000
18,000
THIS CHART BASED ON CABIN HEAT, ENGINE
ANTI−ICE
OFF, ELECTRICAL LOAD 30 AMPERE,
250−C18 ENGINE
REDUCE HOVER WEIGHT CAPABILITY
1. 33 LB WITH PARTICLE SEPARATOR
2. 33 LB WITH SCAVENGE AIR ON
3. 11 LB WITH ENGINE AIR INLET SCREEN 369H8086
4. 50 LB WITH MAIN ROTOR ABRASION TAPE
INSTALLED
INCREASE (OR DECREASE
WEIGHT
CAPABILITY LBS
(ABOVE CRITICAL ALTITUDE)
PER 10 AMPERE REDUCTION
(OR
OAT °C INCR
−
E 5 ASE 1 ) 5 35 IN
6,000
ELECT
W
R
T
ICAL LOA
2
D
5 7
16,000
14,000
12,000
10,000
8,000
5,000
4,000
3,000
6,000
4,000
2,000
* WEIGHT GREATER
THAN 2550 LB MUST
BE EXTERNAL AND
JETTISONABLE
2,000
1,000
0
−
40
−
30
−
20
0
−
10 0 10 20 30 40
AMBIENT TEMPERATURE
−
DEGREES C
NOTE: SOLID LINES REPRESENT HOVER CAPABILITY WITHIN THE LIMITATIONS OF 20 KNOT SIDE WIND. DASHED LINES ARE REPRESENTED FOR
INFORMATION ONLY AND REPRESENT PERFORMANCE CAPABILITY IN ZERO WIND
CONDITIONS.
5−FOOT SKID CLEARANCE WITH EXTENDED LANDING GEAR INSTALLED.
F01
−
032