Radius Of Action And Range Of Flight Over Mountains - Kazan Helicopters Mi-17-1V Flight Manual

M",·17·1B. Flight manual
Tab!e 1.6
Fuel Consumption per Kilometer and Hour at Maximum Flight
r
S d G W . h FI"
nne ;pee versus
ross eun t and
iqht Altitude
lAS, km/h
Gross weiqht, k
9000 10000 11000 12000 13000
E
II
0>
E
-
~
'c 'c 'c 'c 'c
C
c C:
c~
CC
C
c-
CC
af
5.Q
Co Co Co Co
_.><"
Sa
8'E.E 8+"
8'E.E 8g
0.2
8g
0.2 ~R.c
_"0
.caE .cwo uo.E
°aE
Uo.E
~~ 'ffi~ .~ 0 » 0
ill ~
f:
ill ~E
c,
.- 0 ~§~ ~§~ illE~ illE~ illE~ ~§~ ~§~
~§g
i:i:<i:
S:::E
~.o:::
.r~~ .r~~ .r~~ .r~~ .r~~
<Il~
LL..,.>< LL..,.><
LL..,.>< LL..,.>< LL..,.><
100 130 130 3,75 499 3,88 516 4,01 533 4,16 553 4,37
583
500
130 130 3,50
479
3,63
497 3,77 517 3,92 537 4,16 570
1000 130 130 3,27 458 3,41 478 3,58 501 3,71
520 399 558
2000
130 130 2,86
423 3,02 447 3,20 474 3,40 503 3,63 534
3000 120 120 2,76 397 2,96 426 3,22 464 3,35 483 3,73
537
4000 120 120 2,51 377 2,74 411 3,03 455 3,23 485 3,81 571
5000 120
-
2,28 354 2,63 407 3,14 486
- . - -
1.7.5. Radius of Action and Range of flight over mountains.
The radius and range of flight over mountain areas should be calculated with
additional limitations imposed by the conditions of takeoff from and landing on
the elevated field accounted for. In order to make sure that this limitation is re-
spected it is necessary, after normal calculation of the range, to calculate the
helicopter weight for takeoff from or landing on the elevated field.
If the takeoff or landing weight proves to be in excess of the maximum weight,
determine a new refined radius or range to meet the above limitation.
Determine the maximum weights for various procedures of takeoff and landing
proceeding as instructed in Section 1.6.
The helicopter takeoff weight is calculated in accordance with the load to be
transported and the fuel quantity aboard.
The procedure of calculation of the helicopter landing weight depends on the
type of operation. Let us consider, for example, the procedure of calculation
for a flight over a selected range (R).
The helicopter weight at the initial point of horizontal flight segment
IHW
=
TOW - GF - TOF
The helicopter weight at the end of horizontal flight segment
EHW
=
IHW-HFF, where
HFF
=
q- HFR.
HFR
=
R - TaD - LD.
The fuel consumption per kilometre (q) is selected for a helicopter average
gross weight (AGW) for the horizontal flight segment.
AGW
=
IHW - 0,47 qin• HFR, where
qin- fuel consumption per kilometre at IHW.
The helicopter landing weight equals
1-15