Kazan Helicopters Mi-17-1V Flight Manual page 35

Mll-17-1B. Flight manual
Table 2.2
Takeoff wei ht, k Hoverin altitude, m
11100 and below U to 10
Above 11100 I Up to 5
Do not hover within the range of altitudes differing from those indicated in
Table 2.2 down to 110m, except for the cases of extreme urgency.
(3) The maximum speed in horizontal flight with the cargo doors semi-open
(for transportation of the main rotor blades and other bulky cargo items) is
230 km/h, and 200 km/h with the doors removed.
(4) Flying over heavily broken terrain is allowed at an altitude of not less than
20
rn
and lAS not less than 60 km/h.
(5) The minimum allowed altitude is 15 m over even terrain and 150 m for fly-
ing by night.
(6) Turn in hovering at angular rates not exceeding 12 deg/s.
(7) The time of full reversal of the pedals necessary to change the helicopter
sense of rotation should be not less than 3 s.
(8) It is allowed to execute 360-degree turns in hovering near the ground at a
wind speed not exceeding 10 rn/s,
(9) It is allowed to start and stop the main rotor and to execute hovering,
takeoff and landing at wind speeds indicated in Table 2.3.
Table 2 3
(10) TaxIIng
IS
allowed at a Wind speed not exceeding 15 mIs, at
headwind nor exceeding 25
rn/s,
(11) Power-on glide is allowed within the range of speeds indicated in
Table 2.1.
(12) Autorotation glide is allowed within the range of speeds indicated in Table 2.1.
(13) Turns with the main rotor autorotating are allowed with bank angles not
exceeding 20°.
(14) The maximum main rotor speed (read on the tachometer indica-
tor) is allowed for not more than 20 s:
- 101
%
at engine power above cruising 2.
- 103
%
at engine power below cruising 2.
(15) The minimum allowed main rotor speed (speed drop):
In flight in transient conditions is 88
%
(on the indicator) for a period not
exceeding 30 s.
The minimum allowed main rotor speed during autorotation landing is 70
%.
To avoid a main rotor speed drop during execution of various maneuvers
involving acceleration of the engines move the collective pitch control
lever from idle to maximum power within a period of time not less than 5s.
To prevent the main rotor overspeed above the allowed maximum limit
the colleCtive pitch control lever downwards motion rate should not ex-
ceed 1 deg/s (except for the cases of engine failure).
(16) It is allowed to engage the An"346 autopilot altitude channel in horizontal
flight at an altitude not less than 50 m.
(17) It is allowed to execute turns and spirals within the allowed range of air-
speeds at bank angles indicated in Table 2.4.
Maximum allowedwind
speed, m/s
Wind direction
At main rotor startingand At takeoff and landing
stooolno
Headwind 25 25
Right side crosswind 10 10
Left side crosswind
15
10
Tailwind 8 10
..
2-4