Schweizer 300Cb/cbi Flight Manual

Front 1

Section I (General)

Main Rotor Diameter in fts.

Back 1

26.83 ft.

Front 2

Section I (General)

Typer of engine used on the 300CB and 300 CBI

Back 2

Lycoming Horizontally Opposed
300CB - HO-360-C1A
300CBI - HO-360-G1A
4 Cylinders
180 hp at 2700 rpm

Front 3

Section I (General)

Main Rotor RPM Limits
Power on
Power off

Back 3

Power on - 442 to 471 rpm
Power off - 390 to 504

Front 4

Section II (Limitations)

Maximum operating altitudes

Back 4

Maximum operating altitudes:

Take off/Landing - 8,000ft Density Alt.
Enroute - 10,000ft Density Alt.

Front 5

Section II (Limitations)

Maximum Vne

Back 5

Maximum Vne;
At sea level:
94 kt (108mph) IAS;
Doors OFF:
90 kt (104mph) IAS

Front 6

Section II (Limitations)

Maximum Gross Weight in the cabin and glove box

Back 6

Maximum Gross Weight in the cabin:
600 pounds
Glove Box;
20 pounds

Front 7

Section II (Limitations)

Rotor Speed Limitations

Back 7

Power OFF:
504 rpm
Power ON:
390 rpm

Front 8

Section II (Limitations)

Maximum Gross Weight

Back 8

Maximum Gross Weight

1750 lbs

Front 9

Section II (Limitations)

Fuel capacity - STD and AUX. tanks

Back 9

Fuel capacity - Main and Aux. tanks

STD: 35.2 gal. (35.0 Usable);
STD + AUX: 65.2 gal (63.0 Usable).

Front 10

Section III (Emergency Procedures)

Engine Failure - Alt. above 450 ft.

Back 10

1. Lower collective pitch.
2.Enter normal autorotation.
3.Establish a steady glide of 52kt IAS Approximately.
4At an altitude of approximately 50 ft, initiate a flare.
5. At approximately 10 feet, coordinate collective pitch with forward movement of cyclic stick to level aircraft and cushion landing. Make ground contact with aircraft level.

Front 11

Section III (Emergency Procedures)


Engine Failure - Alt. above 7 ft and below 450 ft.

Back 11

Conduct takeoff operation in accordance with the restrictions shown on Height Velocity Diagram.
1. In event of power failure during takeoff, lower collective pitch (altitude permitting), in order to maintain the rotor speed. The amount and duration of collective reduction depends upon the height above the ground at which the engine failure occurs.
2.As the ground is approached, use aft cyclic and collective as needed to decrease forward and vertical velocity.
3.Establish a level attitude prior to ground contact. Apply collective pitch as necessary in order to cushion landing.

Front 12

Section III (Emergency Procedures)

Engine Failure - Below 7 ft.

Back 12

A power failure is indicated by sudden yawing of the ship to the left.
1. Apply right pedal to prevent excessive yawing and right stick to minimize drift.
2. Apply collective pitch as necessary in order to cushion landing.

Front 13

Section III (Emergency Procedures)

Ditching - Power off

Back 13

Follow the procedures for autorotation approach and landing. Upon contact with water, proceed as follow:
1.Lower collective pitch and apply sidewards cyclic stick after contact is made with water.
2.Release seat belt and shoulder harness.
3.Open both doors and exit helicopter.

Front 14

Section III (Emergency Procedures)

Ditching - Power ON

Back 14

1.Descend to hovering altitude over water;
2.Unlatch doors;
3.Passenger exit aircraft;
4.Fly a safe distance away;
5.Turn battery and alternator switches OFF;
6.Close twistgrip to idle position;
7.Allow aircraft to settle in a level altitude, apply full collective;
8.When aircraft begins to roll, reduce collective to full down.
9.Release seatbelt and shoulder harness;
10.When rotor blades have stopped turning, clear aircraft as quickly as possible;

Front 15

Section III (Emergency Procedures)

M/R XMSN TEMP/PRESS

Back 15

A red light comes on when transmission oil pressure drops below 2-1/2 psi or temp. exceeds 235ºF.

Land as soon as possible.

Front 16

Section III (Emergency Procedures)

M/R XMSN CHIPS

Back 16

An amber caution light will come on to indicate possible deterioration of components within the main rotor transmission.
Land as soon as possible.

Front 17

Section III (Emergency Procedures)

T/R XMSN CHIPS

Back 17

An amber caution light will come on to indicate possible deterioration of components within the tail rotor transmission.
Land as soon as possible.

Front 18

Section III (Emergency Procedures)

Low Fuel, Caution Indicator

Back 18

An amber fuel low caution light (FUEL LOW) on the instrument panel comes on in flight when approximately on gallon of usable fuel remains in the tank.
Land immediately.

Front 19

Section III (Emergency Procedures)

Clutch Warning Light

Back 19

A red clutch warning light (RELEASE) is illuminated whenever the clutch is not fully engaged.
Be prepared to enter autorotation.
Land as soon as possible.

Front 20

Section III (Emergency Procedures)

Tail Rotor Failure In Forward Flight

Back 20

Failure is normally indicated by uncontrolled yaw to the right.
1.Reduce power by lowering the collective.
2.Adjust airspeed to 50 to 60 knots.
3.Use left lateral cyclic in combination with collective pitch to limit left slideship to a reasonable angle.
4.If conditions permit, place the twistgrip in the idle position once a landing area is selected, and perform a normal autorotation. Plan touch down with little or no foward speed.

Front 21

Section III (Emergency Procedures)

Tail Rotor Failure While at a Hover

Back 21

Failure is normally indicated by uncontrolled yaw to the right.
While at a hover: Place the twistgrip in the IDLE position and perform a normal hovering autorotation.

Front 22

Section III (Emergency Procedures)

Tail Rotor Control Failure - Fixed Pitch Setting

Back 22

1.Adjust power to maintain 50 to 60 knots airspeed.
2.Perform a shallow approach and running landing to a suitable area, touching down into wind at a speed between ETL and 30 knots. Directional control may be accomplished by small adjustments in throttle and/or collective control.

Front 23

Section III (Emergency Procedures)

Air Restart 300CB

Back 23

If altitude permits:
1.Mixture - FULL RICH;
2.Throttle - CRACK APPROXIMATELY 1/2 AN INCH;
3.Starter - ENGAGE