Oh-58C 5/8/9 Cautions, Notes, & Warnings

Front 1

Engine Oil Pressure
1 Note
1 Caution

Back 1

DISREGARD yellow and green instrument markings for engine oil pressure.

During cold weather start, maximum may go to 150psi, but you must remain at engine idle position until normal limits are attained.

Front 2

Engine Oil Temperature
1 Note

Back 2

During cold weather operations the engine may be operated at engine oil temperatures down to -50 deg C.

Front 3

Transmission Oil Pressure Limits
1 Note

Back 3

Light will remain on until 36 +/- 2 psi is exceeded.

Front 4

Wind Limitations
1 Note

Back 4

Gust spreads are not normally reported. To obtain spread, compare minimum and maximum wind velocity.

Front 5

Fuel Operations Limits
1 Note

Back 5

Engine starting difficulties may be encountered if any fuel other than JP-4 is used at ambient temperatures below +5 deg C

Front 6

Control Movements
1 Caution

Back 6

For gross weights greater than 3000lbs and density altitudes greater than sea level, the directional control margins may be significantly reduced while hovering in winds from the right greater than or for right sideward flight at speeds greater than 20 knots.

Front 7

Flight Restrictions For Practice Autorotation Landings
1 Caution

Back 7

In any event, relatively long ground runs with the collective up, or any tendency to float for long distance prior to skid contact should be avoided. If vibrations are encountered after touchdown immediately lowering the collective is recommended.

Front 8

Flight Restrictions For High Power
1 Note

Back 8

In aircraft equipped with IR exhaust stacks, rate of climb in excess of 1000 ft/min may result in divergent aircraft pitch oscillations which can reach 20 to 30 degree attitudes. This divergence can be alleviated by either increasing airspeed during steady climbs or decreasing rate of climb. Climb rates in excess of 1000 ft/min should be avoided.

Front 9

Slope Landing / Take-off Limitations
1 Caution

Back 9

Caution is to be exercised for slopes greater than 5 degrees since rigging, loading, terrain and wind conditions may alter e slope landing capability. See Rollover characteristics in FM 1-203

Front 10

Flight Over Salt Water
1 Caution

Back 10

Prolonged hovering over salt water which results in spray ingestion, indicated by spray on the windshield, shout be avoided.

Front 11

Chapter 8 loose equipment and seat belts
1 WARNING

Back 11

Demonstrate to passenger how and where loose carry-on equipment will be secured. Demonstrate to passenger hos seat belts and shoulder harnesses are to be used and how they are to be secured when exiting.

Front 12

Chapter 8 Area 5 swashplate
1 Note

Back 12

Ensure swashplate is level for inspection of outer-ring self-aligning bearing for main rotor push-pull tubes.

Front 13

Chapter 8 Engine Start
1 WARNING

Back 13

Do not have battery switch on and APU system charging simultaneously for more that 2 minutes. This will prevent an unmonitored battery from overheating and possibly exploding.

Front 14

Chapter 8 Engine Start
1 Note

Back 14

Do not wait for N1 to peak out. Delay in moving the throttle to engine idle may diminish battery capacity early in the start cycle.

Front 15

Chapter 8 Deceleration Check
1 Note

Back 15

Multiple attempts may be required before proficiency is obtained in timing the deceleration.

Front 16

Chapter 8 Takeoff
1 Caution

Back 16

During takeoff with helicopter skids close to the ground, nose-low attitudes of 10 degrees or more can result in ground contact of the WSPS lower cutter tip. Forward CG, high gross weight, high density altitude, translational lift settling, and tail wind increases the possibility of ground contact.

Front 17

Chapter 8 Engine Shutdown
1 Caution

Back 17

If throttle is inadvertently rolled to close position, do not attempt to roll it back on

Front 18

Chapter 8 Engine Shutdown Seat Belt
1 Caution

Back 18

Do not drop seat belt against side of aircraft. Buckles and bracket will damage honeycomb panel under crew member door frame.

Front 19

Chapter 8 Loss Of Tail Rotor Effectiveness
1 Note

Back 19

The pilot must anticipate these variation, concentrate on flying the aircraft, and not allow a yaw rate to build.

Front 20

Chapter 8 Adverse Environmental Conditions, Controls
1 Caution.

Back 20

Check that all surfaces and controls are free of ice and snow

Front 21

Chapter 8 Adverse Environmental Conditions, Fluids
1 Note.

Back 21

Contraction of the fluids in the helicopter system at extreme low temperature causes indication of low levels. A check made just after the previous shutdown and carried forward to the walk-around check is satisfactory, if no leaks are in evidence. Filling, when the system is cold-soaked, reveals an over full condition immediately after flight, with the possibility of forced leaks at seals.

Front 22

Chapter 8 Adverse Environmental Conditions, Fuel
1 Caution.

Back 22

In the fuel system, condensation and freezing of moisture in pneumatic circuits can occur when weather conditions of low temperature and high relative humidity are encountered. This condition can cause auto acceleration of engine.

Front 23

Chapter 8 Adverse Environmental Conditions, Fuel
1st Note.

Back 23

Auto acceleration resulting from frozen moisture in fuel system air circuits dose not repeat unless aircraft is again subjected to cold soak. to prevent icing/auto acceleration, make a 10 minute ground warm-up run at idle before flight. This warm-up is recommended when aircraft has been allowed to cold soak in low ambient temperatures of -12deg C or below and high relative humidity of 45% or greater.

Front 24

Chapter 8 Adverse Environmental Conditions, Fluids
2nd Note.

Back 24

Due to variation in types of jet fuel, in cold weather the engine may experience a short delay before light off after the throttle is advanced to idle position. This delay should be less than three seconds, regardless of the type of fuel used.

Front 25

Chapter 8 Cold Weather Starts Engine Oil Pressure
1 Note.

Back 25

During cold weather starting, the engine oil pressure gauge may exceed 130 PSI. The engine should be warmed up at engine idle until the engine oil pressure indication is below 130 PSI

Front 26

Chapter 8 Adverse Environmental Conditions, Controls Check
1 Warning.

Back 26

Control system checks should be performed with extreme caution when helicopter is parked on snow and ice. There is reduction in ground friction holding the helicopter stationary; controls are sensitive and response is immediate.

Front 27

Chapter 8 Thunderstorms
1 WARNING

Back 27

Avoid flight in or near thunderstorms, especially in area of observed or anticipated lightning discharges.

Front 28

Chapter 8 Rotor Damage
1 Note

Back 28

Abnormal operating noises almost always accompany rotor damage, but loudness or pitch are not valid indication of degree of damage sustained.

Front 29

Chapter 8 Rotor Ice
1 WARNING

Back 29

Ice shed from rotor blades and/or other rotating components presents a hazard to personnel during landing and shutdown. Ground personnel should remain clear of helicopter during landing and shutdown; passengers/crew members should not exit aircraft until rotor has stopped turning.

Front 30

Immediate Action Emergency Steps
1 Note (Part I)

Back 30

The urgency of certain emergencies requires and immediate and instinctive action the the pilot. The most important single consideration is helicopter control. All other procedure are subordinate to the requirement.

Front 31

Immediate Action Emergency Steps
1 Note (Part II)

Back 31

The MASTER CAUTION should be reset after each malfunction to allow system to respond to subsequent malfunctions. If time permits during a critical emergency, transmit a MAYDAY call, set transponder to emergency, jettison external store if appropriate, and lock shoulder harnesses.

Front 32

EMERGENCY SHUTDOWN
1 Note

Back 32

Total electrical failure in the OH-58C will result in loss of rotor RPM indications.

Front 33

Engine Malfunction- Partial or Complete Power Loss
1 Note

Back 33

Under any partial power condition, the throttle should be checked to ensure it is full open and, time and altitude permitting, the GOV RPM switch may be increased to ensure maximum RPM is applied.

Front 34

Engine Malfunction- Partial or Complete Power Loss
1 WARNING

Back 34

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 that 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.

Front 35

Complete Loss Of Tail Rotor Thrust
1 WARNING

Back 35

Degree of roll and sideslip may be varied by varying throttle and/or collective (At airspeed below 40 knots in powered flight, the sideslip may become uncontrollable, and the helicopter will begin to spin on the vertical axis. Autorotation may be the only option)

Front 36

Loss Of Tail Rotor Effectiveness (LTE)
1 WARNING

Back 36

Collective reduction will aid in arresting the yaw rate; however, if a rate of decent has been established, collective reduction may increase the rate of descent to an excessive value. The resultant large and rapid increase in collective to prevent ground or obstacle contact may further increase the yaw rate, decrease the rotor RPM and cause an over torque and/or over-temperature condition. Therefore, the decision to reduce collective must be based on the pilot assessment of the altitude available for recovery.

Front 37

Fire
1 WARNING

Back 37

Toxic fumes of the extinguishing agent may cause injury, and liquid agent may cause frostbite or low temperature burns.

Front 38

Fire
1 Caution

Back 38

If aircraft fire occurs on ground while using Ground Power Unit (GPU); the GPU should be shutdown immediately.

Front 39

Hot Start
1 Caution

Back 39

During engine starts using a Ground Power Unit (GPU), failure of the GPU could possibly result in an engine hot start. after GPU failure during start, the pilot must turn the battery switch on before accomplishing the procedure described below.

Front 40

Smoke And Fume Elimination
1 Caution

Back 40

Do not jettison doors in flight above effective translational lift.

Front 41

Overheated Battery
1 WARNING

Back 41

Do not open battery compartment or attempt to disconnect or remove overheated battery. Battery fluid will cause burns and overheated battery will cause thermal burns and may explode.

Front 42

Hydraulic System Failure
1 WARNING

Back 42

Do not return the HYD BOOST switch to the ON position for the remainder of the flight. This prevents any possibility of a surge in hydraulic pressure and the resulting loss of control.