Failure Of Two Engines. Autorotation Landing - Kazan Helicopters Mi-17-1V Flight Manual

M,,·17·1B. Flight manual
Table 6 2
Altitude (pressure), m
Hourly fuelflow, kg/h
Normal aross weiaht Maximum arossweiaht
500 515 550
1000 460 460
2000 410
-
3000 360
-
In all cases when one engine fails in flight and it proves impossible to execute
horizontal flight with one engine operating at contingency power select a
landing area and land thereon.
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11
12
TOW,
tons
13
·30
·20
·10
o
10
20 30
400AT,OC
Fig. 6.1. Maximum Helicopter Weight in Horizontal Flight with One Engine In
operative IAS=120km/h (Anti-Icing off).
_ _ 2.5 - minpower
_____30 - minpower
6.2. Failure of two engines. Autorotation landing
(1) Indications:
(a) Sudden out-of-trim condition of the helicopter appearing as a sharp
helicopter jerk to the right. The magnitude of out-of-trim condition
depends on the airspeed (the higher is power setting and the less is
the airspeed the more is abrupt occurrence of the out-of-trim condi-
tiM).
(b) Change of noise pitch of the engines.
(c) Sharp main rotor speed drop.
(d) Drop of R.P.M. and TGT of both engines.
(2) Crew's actions:
(a) If the engines fail at altitudes above 100 m and airspeed above 80
km/h immediately establish autorotation, for this purpose proceed
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