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a. Indications:.
(1) Varying degrees of right yaw depending on
power applied and airspeed at time of failure,
(2) Forward CG shift.
(3) Abnormal vibrations.
b. Procedures:.
(1) Enter autorotative descent (power off).
(2) Maintain airspeed above minimum rate of
descent airspeed.
TM 1-1520-248-10
The safety of helicopter occupants is the primary
consideration in the event a fire occurs; therefore, it is
imperative that every effort be made by the flight crew
to extinguish the fire. On the ground, it is essential that
the engine be shut down, crew evacuated, and fire
fighting begun immediately. Time permitting, a
MAYDAY call should be transmitted before electrical
power is turned off to expedite assistance from airfield
fire fighting equipment and personnel. If the helicopter
is in flight when the fire occurs, the most important
action is to land the helicopter.
9-33. ABORT START/HOT START/RESIDUAL
FIRE.
During engine starting or shutdown if any limits are
exceeded or if it becomes apparent that limits may be
exceeded, proceed as follows:
CAUTION
To prevent engine damage, do not
depend on the FADEC system to monitor
the starter automatically during an
aborted start. In a low battery voltage
condition, the ECU may not operate
properly.
NOTE
During engine starting the FADEC
system monitors engine parameters and
will automatically abort the start if it
becomes apparent that TGT limits may be
exceeded. It will continue to motor the
starter for 60 seconds or until TGT is
below 149 °C.
Abort sequence begins at 843 °C for most
operations. However, it will begin at 913
°C if pressure attitude is greater than
10000 feet or if residual TGT is greater
than 82.2 °C at initiation of engine start.
1. Throttle – Close.
2. START switch – ON and hold until TGT is
less than 200 °C.
(3) If run-on landing is possible complete
autorotation with a touchdown airspeed as required for
directional control.
(4) If run-on landing is not possible, start to
decelerate from about 100 feet altitude so that forward
groundspeed is at a minimum when the helicopter
reaches 10 to 20 feet: execute the termination with a
rapid collective pull just prior to touchdown in a level
attitude with minimum ground speed.
9-29. MAIN DRIVESHAFT FAILURE.
Failure of the main driveshaft will be evidenced by a
Sudden increase in engine rpm (NP), decrease in rotor
Rpm (NR), and left yaw. In addition, the LOW RPM
ROTOR warning message will be displayed and
Accompanying audio warning will sound. In the event of
Main driveshaft failure:
NOTE
The engine must continue to operate in
order to provide tail rotor control.
1. AUTOROTATE – Throttle full open.
2. EMER SHUTDOWN after landing.
9-30. CLUTCH FAILS TO DISENGAGE.
A clutch failing to disengage in flight will be indicated
by rotor rpm decaying with engine rpm as the throttle is
reduced when entering autorotation. This condition
results in total loss of autorotational capability. If a
failure occurs:
1. Throttle – Open.
2. LAND AS SOON AS POSSIBLE.
9-31. CLUTCH FAILS TO RE-ENGAGE.
During recovery from autorotation descent, clutch
malfunction may occur and will be indicated by a
decrease in NR with NP remaining constant. If failure
occurs:
1. AUTOROTATE.
2. EMER SHUTDOWN.
9-23. FIRE.
WARNING
Toxic fumes of the extinguishing agent
may cause injury. Liquid agent may
cause frostbite or low-temperature burns.
9-22
TM 1-1520-248-10
9-34. ENGINE/FUSELAGE/ELECTRICAL FIRE
- GROUND.
EMER SHUTDOWN.
9-35. ENGINE/FUSELAGE/FIRE – LOW/
CRUISE ALTITUDE.
If a fire is observed during flight, prevailing
circumstances such as: VMC, IMC, night, altitude, and
landing areas available must be considered in order to
determine whether to execute a power-on or power-off
landing.
a. If power-on landing:
1. LAND AS SOON AS POSSIBLE.
2. EMER SHUTDOWN after landing.
b. If power-off landing:
1. AUTOROTATE.
2. EMER SHUTDOWN. Accomplish during
descent if time permits.
9-36. ELECTRICAL FIRE FLIGHT.
Prior to shutting off all electrical power, the pilot must
consider the equipment that is essential to a particular
flight environment that will be encountered, e.g., flight
instruments, fuel boost pump, and automatic fuel
control systems.
In the event of electrical fire or suspected electrical fire
In flight:
1. AC and DC GEN switches – OFF.
　
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