4,000' @ 40C HOGE (1hr fuel onboard)
MD500E
MD530F Plus AS350B2
Bell 407
AS350B3
GROSS WT
2720
3360
4610
4640
5260
BEW
1556
1660
2765
2751
2791
PILOT
200
200
200
200
200
FUEL (1hr)
190
231
319
299
333
Useful Load
774
1269
1326
1390
1936
28
34
47
44
49
Fuel: Gal/Hr
ROTORCRAFT FLIGHT MANUAL
CSP–E–1
Additional Operations
and Performance Data
MCDONNELL DOUGLAS
McDonnell Douglas Helicopter Systems
MD500E
THIS CHART BASED ON WINDS LESS THAN 3 KNOTS, CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE,
APPLICABLE TO PARTICAL SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET.
REDUCE WEIGHT:
1. 55 LB WITH SCAVENGE ON
2. 40 LB WITH MIST ELIMINATOR INSTALLED
INCREASE WEIGHT:
DECREASE WEIGHT:
INCREASE (OR DECREASE) WT.
CAPABILITY LBS (ABOVE CRITICAL
ALTITUDE) PER 10 AMP REDUCTION (OR
INCREASE) IN ELECTRICAL LOAD
16000
NOT VERIFIED WHEN MAIN ROTOR
BLADES HAVING ABRASION STRIPS
ARE INSTALLED
14000
OAT°C −5
DWT
1
15
2
35
3
MAXIMUM INTERNAL
GROSS WEIGHT
12000
PRESSURE ALTITUDE − FEET
50 LB WITH ABRASION STRIPS ON
MAIN ROTOR BLADES ONLY
50 LB WITH ABRASION STRIPS ON
TAIL ROTOR BLADES ONLY
GROSS WEIGHTS ABOVE
3000 LB MUST BE EXTERNAL
AND JETTISONABLE
10000
8000
6000
4000
REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:
(APPLICABLE TO ALL TEMPERATURES)
PRESSURE
ALT. FT.
SL TO 4000
8000
12000
16000
2000
0
2000
2200
4,000'@ 40C
CABIN
HEAT
220
152
111
86
ANTI−
ICE
232
157
117
89
2400
BOTH
469
306
227
172
2600
2,720 LBS
2800
3000
3200
3400
GROSS WEIGHT − POUNDS
3600
F03–044–1
<<<< ALLISON 250−C20B >>>>
Figure 8–1. Hover Ceiling Versus Gross Weight, Out of Ground Effect,
Takeoff Power, Two or Four Bladed Tail Rotor,
Allison 250–C20B
28gal/hr X 6.8lbs/gal = 190lbs/hr
8–2
Revision 10
−5
15
35
3
9
14
MAXIMUM GROSS WEIGHT
INTERNAL LOAD OPERATION
NO WIND
HOT DAY (ISA + 23 ° C)
Additional Operations
and Performance Data
REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:
(APPLICABLE TO ALL TEMPERATURES)
PRESSURE
ALT. FT.
SL TO 6000
8000
12000
16000
−30 −20 −10
0 10 20 30
OAT − DEG C
4,000'@ 40C
40
50
ANTI−
ICE
0
0
0
90
2600
CABIN
HEAT
0
0
335
450
BOTH
2800
3000
0
100
510
603
3200
3400
3600
GROSS WEIGHT − LB
F40–034
Original
D WEIGHT
CONTROLLABILITY LIMIT − 3 PERCENT
PEDAL MARGIN IN 17− KT SIDEWIND FROM
THE RIGHT REAR QUARTER
ROTORCRAFT FLIGHT MANUAL
CSP–FF–1
OAT,° C
3800
3,360 LBS
34gal/hr X 6.8lbs/gal = 231lbs/hr
8–2
CAUTION: ADEQUATE COOLING
HAS BEEN DEMONSTRATED UP TO
8800 FT FOR HOT DAY (ISA + 20° C)
AVOIOD PROLONGED HOVER ABOVE
THIS ALTITUDE.
EXAMPLE:
PRESS. ALT −−−−−−−−− 8000 FT
OAT−−−−−−−−−−−−−−−− 6 ° C
ENTER CHART AT 6 °C ON OAT SCALE
MOVE UP TO 8000 PRESS. ALT LINE,
MOVE RIGHT TO GROSS WEIGHT LINE,
READ HOVER GROSS WEIGHT = 3420 LB
INCREASE (OR DECREASE) WEIGHT
CAPABILITY POUNDS (ABOVE CRITICAL
ALTITUDE) PER 10 AMPERE REDUCTION
(OR INCREASE) IN ELECTRICAL LOAD
Figure 8–1. Hover Ceiling, OGE, Standard Engine Air Inlet
McDonnell Douglas Helicopter Systems
MCDONNELL DOUGLAS
MD530F Plus
r
;
; j
;
,
AS350-B2
FLIGHT MANUAL
6 HOVER
PERFORMANCE
O.G.E.
.
20000
~
6000
18000
~
+'
---
E
w 16000
5000
:)Q
6
.00
I-
00
~
.UJ
~ 14000
'~
~
I/)
~
f
4000
g .
'I-
I/)
w 12000
~
1
l-
ll:
-1
Q.
([
"
10000
~
3000
~
0
8000
2000
6000
4000
0
2000
"0
1000
0
~0
~~
0
"'0
'"
2: -1000
0
.
-305
_1~02
3000
' ,
35100 ..40.00
2202 _'-,;~~
..45100'
"sb1oo ~k~)
' (l'b;~5?0
MASSE
WEIGHT
4,000'@40C
~
4,610 LBS
CONDITIONS
f«>VERPERFORMANCE
-No
-No
wind
P2 air
O.G.E,
bleed
DGAC
Approved:
m
350
B2
47gal/hr X 6.8lbs/gal = 319lbs/hr
~.jl.
89-17
Page6
BHT-407-FM-1
TC APPROVED
HOVER CEILING
OUT OF GROUND EFFECT
SKID HEIGHT 40 FT (12.2 METER)
HEATER AND ANTI-ICE OFF
BASIC INLET
TAKEOFF POWER
ENGINE RPM 100%
GENERATOR 180 AMPS
NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART
GROSS WEIGHT - KG x 100
16
20
,0
00
20,000 FT HD
20
REFER TO
FIG. 4-5B
,0
00
24
16
,0
26
MAX DEMONSTRATED HD
AREA B
14
,0
00
REFER TO
FIG. 4-5A
14,000 FT HD
00
0
0
-3
°C
0
0
-4
60
00
30
T
OA
80
00
-
0
-1
20
10
,0
00
T
OA
0
-2
12
,
10
UM
XIM
MA
T
UM OA
MAXIM
MINIMUM OAT
22
17,000 FT HD
00
18
18
20
40
OAT - °C
4,000'@40C
60 32
36
40
44
48
17 DEC 2002
52
56
60
GROSS WEIGHT - LBS x 100
4,640LBS
M407_FM-1__FIG_4-7_(1_OF_8).WMF
Figure 4-7. Hover ceiling OGE (sheet 1 of 8)
4-22
EXTERNAL = 6000 LB
MAX GW
INTERNAL = 5000 LB
-2
0
00
LE
VE
L
20
SE
A
-F
T
P
H
0
.7
51
-20
50
00
40
00
40
-40
REFER TO
FIG. 4-5
44gal/hr X 6.8lbs/gal = 299 lbs/hr
AS350-B3
FLIGHT
MANUAL
.CONDITIONS
OGE HOVERING
FLIGHT PERFORMANCE
7
.22
20
6
.18
18
5
0 14
;0
0
2
x
4-0x
::
E
-12
.:..
Q.
Q.
Z
Z
10
3
8
6
.4
0
0
::j
~
s
..
m
"::
~
>
w
.
2
0
1200
3000
3500
4000
200
400
5000
5500
6000
(Ib)
WEIGHT
4,000'@ 40C
5,260 LBS
Figure 3
OGAC
Approved:
IA I 8 I CIF I
35083
5.1
97-40
49gal/hr. x 6.8lbs/gal= 333 lbs/hr
Page 7