NOTE
The urgency of certain emergencies requires immediate and instinctive action by the pilot. The most important single consideration is aircraft control. All procedures are subordinate to this requirement.
a. The term LAND AS SOON AS POSSIBLE is defined as executing a landing to the nearest suitable landing area without delay. The primary consideration is to assure the survival of occupants.
b. The term LAND AS SOON AS PRACTICABLE is defined as executing a landing to a suitable airfield, heliport, or other landing area as the situation dictates.
1 . COLLECTIVE ADJUST as required to maintain rotor RPM.
2. PEDALS ADJUST as required.
3. THROTTLE ADJUST as required.
4. AIRSPEED ADJUST as required.
1. THROTTLE – OFF.
2. FUEL switches – OFF.
3. BAT switch – OFF.
Because automatic acceleration, deceleration, and overspeed control are not provided with the GOV switch in the EMER position, throttle and collective coordinated control movements must be smooth to prevent compressor stall, overspeed, overtemperature, or engine failure.
CAUTION
No more than 42 PSI torque is available when the GOV AUTO/EMER switch is in the EMER position due to limited fuel flow and may be significantly reduced based on ambient conditions.
1. GOV – switch EMER.
2. Throttle – Adjust as necessary to control RPM.
3. Land as soon as possible.
a. Cockpit Doors.
(1) Pull handle.
(2) Push door out.
b. Cabin Door Windows.
(1) Pull handle.
(2) Lift window inward.
Toxic fumes of the extinguishing agent may cause injury, and liquid agent may cause frost bite or low-temperature burns.
Refer to figure 9-1 for fire extinguisher and first aid kit locations.
Maximum Glide Distance
See figure 9-2, or 9-8.
See figure 9-2
Maximum Glide Distance
See figure 9-2 or 9-8.
Land as soon as possible.
Partial or Complete
b. Flight characteristics:
(2)-Airspeed above the minimum rate of descent values (figures 9-2) will result in greater rates of descent and should only be used as necessary to extend glide distance.
(3)-Airspeeds below minimum rate of descent airspeeds will increase rate of descent and decrease glide distance.
(4)-Should the engine malfunction during a left bank maneuver, right cyclic input to level the aircraft must be made simultaneously with collective pitch adjustment. If the collective pitch is decreased without a corresponding right cyclic input, the helicopter will pitch down and the roll rate will increase rapidly, resulting in a significant loss of altitude.
WARNING
Do not close the throttle. Do not respond to the rpm audio and/or warning light illumination without first confirming engine malfunction by one or more of the other indications. Normal indications signify the engine is functioning properly and that there is a tachometer generator failure or an open circuit to the warning system, rather than an actual engine malfunction.
If time permits, during the autorotative descent, transmit a “May Day” call, set transponder to emergency, jettison external stores, and lock shoulder harness.
9-11. Engine Malfunction- Hover
2. EMER GOV OPNS
1. Throttle – Off.
2. STARTER GEN switch – START.
3. FUEL switches – ON.
4. GOV switch – EMER.
5. Attempt start.
a. Starter switch— Press.
b. Throttle- Open slowly to 6400 to 6600 rpm as N1 passes through 8 percent. Control rate of throttle application as necessary to prevent exceeding EQT limits.
c. Starter switch- Release as N1 passes through 40 percent. After the engine is started and powered flight is reestablished, continue with manual control. Turn the START FUEL switch OFF and return the STARTER GEN switch to STANDBY.
6. Land as soon as possible.
Droop Compensator Failure
EMER GOV OPNS
Engine Compressor Stall
1. Collective – Reduce .
2. DE-ICE and BLEED AIR switches – OFF.
3. Land as soon as possible.
Inlet Guide Vane Actuator Failure – Close position
Inlet Guide Vane Actuator Failure – Open position
Engine Overspeed
2. Throttle—Reduce until normal operating rpm is attained. Continue with manual throttle control.
If reduction of throttle does not reduce rpm as required:
3. EMER GOV OPNS
Transmission Oil-Hot or Low Pressure
1. Land as soon as possible.
2. EMER SHUTDOWN- After landing.
Engine operating RPM, with zero to near zero torque must be maintained throughout the approach. Torque applied for landing should be used at low altitudes to aid in preventing seizure of gears in the transmission.
Tall Rotor Malfunctions
Complete Lost off Tall Rotor Thrust.
a. Indications.
(1 ) Pedal input has no effect on helicopter trim.
(2) Nose of the helicopter turns to the right (left sideslip).
(3) Roll of fuselage along the longitudinal axis.
(4) Nose down tucking will also be present.
WARNING
At airspeeds below 30 to 40 knots, the sideslip may become uncontrollable, and the helicopter will begin to revolve on the vertical axis (right or left depending on power, gross weight, etc).
Procedures 1 to 4
(1) If safe landing area is not immediately available and powered flight is possible, continue flight to a suitable landing area at above minimum rate of descent airspeed. Degree of roll and sideslip may be varied by varying throttle and/or collective.
(2) When landing area is reached, AUTOROTATE using an airspeed above minimum rate of descent airspeed.
(3) If landing area is suitable, touchdown above effective translational lift utilizing throttle as necessary to maintain directional control.
(4) If run-on landing is not possible, start to decelerate at about 75 feet altitude so that forward groundspeed is at a minimum when the helicopter reaches 10 to 20 feet; execute the touchdown with a rapid collective pull just prior to touchdown in a level attitude with minimum groundspeed.
Fixed Pitch Settings
Reduced power (low torque).
(1) Indications: The nose of the helicopter will turn right when power is applied.
(2) Procedure: Reduced power situations:
(a) If helicopter control can be maintained in powered flight, the best solution is to maintain control with power and accomplish a run-on landing as soon as practicable.
(b) If helicopter control cannot be maintained, close the throttle immediately and accomplish an autorotational landing.
Increased power
(high torque).
(1) Indications: The nose of the helicopter will turn left when power is reduced.
(2) Procedure.
(a) Maintain control with power and airspeed be tween 40 and 70 knots.
(b) If needed, reduce rpm (not below 6000) to control sideslip.
(c) Continue powered flight to a suitable landing area where a run-on landing can be accomplished.
(d) On final, reduce rpm to 6000 and accomplish a run-on landing.
At a Hover
(1) Indication. Helicopter heading cannot be controlled with pedals.
(2) Procedure.
(a) Fixed Pedal Land.
(b) Loss of tail rotor thrust— AUTOROTATE.
Loss of Tail Rotor Components
Indications
(1) Varying degrees of right yaw depending on power applied and airspeed at time of failure.
(2) Forward CQ shift.
Procedure
(1) Enter autorotative descent (power off).
(2) Maintain airspeed above minimum rate of descent airspeed.
(3) If run-on landing is possible, complete autorotation with a touchdown airspeed of between 15 and 25 knots.
(4) If run-on landing is not possible, start to decelerate from about 75 feet altitude, so that forward groundspeed is at a minimum when the helicopter reaches 10 to 20 feet; execute the touchdown with a rapid collective pull just prior to touchdown in a level attitude with minimum ground roll.
Loss of Tail Rotor Effectiveness
a. Out-of-ground effect hover.
b. High pressure altitude/high temperature.
c. Adverse wind conditions.
d. Engine/rotor rpm below 6600/324.
e. Improperly rigged tail rotor.
f. High gross weight.
Indications / Procedures
(2) Procedures. Lower collective to regain control and allow the aircraft to touchdown with little if any forward movement.
Main Drtveshaft Failure
1. Autorotate.
2. EMER SHUTDOWN.
Clutch Falls to Disengage
1. Throttle – On.
2. Land as soon as possible.
Clutch Fails to Re-engage
1. Autorotate.
2. EMERGENCY SHUTDOWN.
Collective Bounce
1. Relax pressure on collective. (Do not “stiff arm” the collective.)
2. Make a significant collective application either up or down.
3. Increase collective friction.
Fire
Flre-Engine Start
1 . Start switch- Press. The starter switch must be held until EGT is in the normal operating range.
2. Throttle— Off. The throttle must be closed im mediately as the starter switch is pressed. 3. FUEL switches-OFF.
Fire-Ground
Fire-Flight
Power-On.
1 . Land as soon as possible.
2. EMER SHUTDOWN after landing.
Power-Off.
1. Autorotate.
2. EMER SHUTDOWN.
Electrical Fire-Flight
1. BAT, STBY and MAlN GEN switches – OFF.
2. Land as soon as possible.
3. Circuit breakers- Out. As each of the following steps is accomplished, check for indications of the source of the fire.
4. MAlN GEN switch-ON.
5. STARTER GEN switch-STBY GEN.
6. BAT switch-ON.
7. Circuit breakers In one at a time in the priority required, GEN BUS RESET first. When malfunctioning circuit is identified, pull the applicable circuit breaker out.
Overheated Battery.
WARNING
Do not open battery compartment or at tempt to disconnect or remove overheated battery. Battery fluid will cause burns and overheated battery will cause thermal burns and may explode.
1. BAT switch OFF.
2. Land as soon as possible.
3. EMER SHUTDOWN after landing.
Smoke and Fume Elimination
Doors, windows, and vents Open.
CAUTION
Do not jettison doors in flight.
Hydraulic
WARNING
During actual or simulated hydraulic failure, do not pull or push circuit breakers or move the HYD CONT switch during takeoff, nap of the earth flying, approach and landing or while the aircraft is not in level flight. This prevents any possibility of a surge in hydraulic pressure and the resulting loss of control.
Hydraulic Power Failure
1. Airspeed Adjust as necessary to attain the most comfortable level of control movements.
2. HYD CONT circuit breaker Out.
If hydraulic power is not restored:
3. HYD CONT circuit breaker – In.
4. HYD CONT switch – OFF.
5. Land as soon as practicable at an area that will permit a run-on landing with power. Maintain airspeed at or above effective translational lift until touchdown.
Control Stiffness
1. HYD CONT switch – OFF then ON. Check for restoration of normal flight control.
If control response is not restored:
If control response is not restored:
2. HYD CONT switch — Off if normal operation is not restored.
3. Land as soon as practicable at an area that will permit a run-on landing with power. Maintain airspeed at or above effective translational lift until touchdown.
Cyclic Hardover
Procedure
2. Land as soon as practicable at an area that will permit a run-on landing with power. Maintain airspeed at or above effective translational lift at touchdown.
Flight Control/Main Rotor System Malfunction.
WARNING/Procedures
Danger exists that the main rotor system could collapse or separate from the aircraft after landing. A decision must be made whether occupant egress occurs before or after the rotor has stopped.
1. Land as soon as possible.
2. EMER SHUTDOWN after landing.
Mast Bumping
1. Reduce severity of maneuver.
2. Land as soon as possible.
Fuel System
9-43.
Fuel Boost Pump Failure
1 . Check fuel pressure. If fuel pressure is zero:
2. Descend to a pressure altitude of 4600 feet or less if possible.
3. Land as soon as practicable.
No attempt should be made to troubleshoot the system while in flight.
20 Minutes Fuel Caution Light ON
Electrical System
9-45.
Main Generator Malfunction
Procedure / NOTE
2. MAIN GEN switch RESET then ON.
Do not hold the switch in the RESET POSITION. If the main generator is not restored or if it goes off again:
3. MAIN GEN switch OFF.
NOTE
Check that the standby generator load- meter is indicating a load. Flight may be continued using the standby generator.
1 . Cockpit doors-Jettison at a hover.
2. Cabin doors-Open.
3. Crew (except pilot) and passengers-Exit.
4. Hover a safe distance away from personnel.
5. Throttle-Off and autorotate. Apply full collective pitch prior to the main rotor blades entering the water. Maintain a level attitude as the helicopter sinks and until it begins to roll, then apply cyclic in direction of the roll.
6. Pilot-Exit when the main rotor is stopped.
1. Cockpit doors Jettison.
2. Cabin Doors Open.
3. Exit when main rotor has stopped.
XMSM OIL PRESS
XMSM OIL HOT
Land as soon as possible. (Ref to para 9-1 9)
Land as soon as possible. (Ref to para 9-19)
RIGHT FUEL BOOST
Land as soon as practicable.
IFF
Information/System Status.
ENGINE ICE DET
Land as soon as possible.
ENGINE ICING
Land as soon as possible.
HYD PRESSURE
Land as soon as practicable.