CSP
−
E
−
1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD 500E
(Model 369E)
Revision 14
3
−
3
FAA Approved
3
−
3. ENGINE FAILURE
COMPLETE POWER LOSS
Indications:
Red
ENGINE
OUT
warning indicator ON and audible warning in headset.
Left yaw (due to a reduction in torque)
Drop in engine speed.
Drop in rotor speed.
Change in noise level.
NOTE
:
The amount of yaw is dependent upon the amount of torque at the moment of
power loss. High torque will cause a large yaw while low torque will cause a
relatively small yaw.
Respond immediately to the ENGINE OUT/low rotor RPM warning by
adjusting collective to maintain rotor RPM within limits, then check
engine instruments and other indications to confirm engine trouble.
Conditions:
The failure indicators are actuated when N
1
falls below 55% or N
R
falls
below 468 N
R
(Ref. 98
±
1% N
2
).
Procedures:
Engine Failure − In Cruise at 500 Feet AGL or Above
Adjust collective pitch according to altitude and airspeed to maintain rotor
speed between 410 and 523 RPM.
Apply pedal pressure as necessary to control aircraft yaw.
Adjust cyclic control as necessary to control airspeed and flight path. Al-
low airspeed to stabilize at 130 Knots IAS or lower (refer to V
NE
plac-
ards).
NOTE
:
At airspeeds above maximum autorotational V
NE
(130 KIAS or less Ref. Section II
V
NE
Placards), use aft cyclic to maintain aircraft’s attitude and slow to desired
airspeed as collective pitch is lowered. Increase collective as necessary after
entering autorotation to prevent rotor overspeed. If desired, operate at minimum
rotor speed to reduce rate of descent and/or extend glide distance.
The minimum rate of descent with power off will be attained at 60 KIAS and 410 N
R
.
WARNING
