Cessna 310 1975 - User Manual

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Cessna®
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MORE PEOPLE BUY AND
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FLY CESSNA AIRPLANES
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THAN ANY OTHER MAKE
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'--' 1975
WORLD'S LARGEST PRO-
DUCER OF GENERAL
AVIATION AIRCRAFT
SINCE 1956
MODEL
310
OWNER'S
MANUAL

Summary

SECTION I OPERATING CHECKLIST

PREFLIGHT INSPECTION

STARTING ENGINES (Left Engine First)

BEFORE TAKEOFF

TAKEOFF

MAXIMUM PERFORMANCE TAKEOFF

CLIMB

CRUISING

BEFORE LANDING

LANDING

GO-AROUND (Multi-Engine)

SECTION II DESCRIPTION AND OPERATING DETAILS

PREFLIGHT INSPECTION

Detailed description of preflight checks and aircraft condition assessment.

STARTING ENGINES

FUEL SYSTEM

ELECTRICAL SYSTEM

LANDING GEAR SYSTEM

LANDING GEAR WILL NOT EXTEND ELECTRICALLY

Manual procedure for extending landing gear when electric system fails.

HEATING, VENTILATING AND DEFROSTING SYSTEM

SECTION III EMERGENCY PROCEDURES

ENGINE INOPERATIVE PROCEDURES

Procedures for engine failure during flight and takeoff.

ENGINE FAILURE DURING FLIGHT

ENGINE RESTARTS IN FLIGHT (After Feathering)

FIRE PROCEDURES

MAXIMUM GLIDE

SINGLE-ENGINE APPROACH AND LANDING

FORCED LANDING

(Precautionary Landing with Power)

Procedure for a precautionary landing with engine power available.

FORCED LANDING (Complete Power Loss)

SYSTEM EMERGENCY PROCEDURES

ENGINE DRIVEN FUEL PUMP FAILURE

Procedure for engine-driven fuel pump failure.

ALTERNATOR FAILURE (SINGLE)

ALTERNATOR FAILURE (DUAL)

LANDING GEAR WILL NOT RETRACT ELECTRICALLY

LANDING EMERGENCIES

LANDING WITH FLAT MAIN GEAR TIRE

Procedure for landing with a flat main gear tire.

LANDING WITH FLAT NOSE GEAR TIRE

LANDING WITH DEFECTIVE MAIN GEAR

LANDING WITH DEFECTIVE NOSE GEAR

DITCHING

SECTION IV OPERATING LIMITATIONS

AIRSPEED LIMITATIONS (CAS)

ENGINE OPERATION LIMITATIONS

WEIGHT AND BALANCE

LOADING CHART

CENTER OF GRAVITY MOMENT ENVELOPE

INSPECTION REQUIREMENTS

SERVICING REQUIREMENTS

SECTION VI OPERATIONAL DATA

NORMAL TAKEOFF DISTANCE

ACCELERATE STOP DISTANCE

DISTANCE TO ACCELERATE STOP VERSUS DECISION SPEED

SINGLE ENGINE TAKEOFF DISTANCE

MULTI-ENGINE CLIMB DATA AT 5500 POUNDS

MAXIMUM PERFORMANCE TAKEOFF 15° FLAPS

SINGLE ENGINE CLIMB DATA

SINGLE ENGINE SERVICE CEILING

CRUISE PERFORMANCE WITH RECOMMENDED LEAN MIXTURE AT 2500 FT

CRUISE PERFORMANCE WITH RECOMMENDED LEAN MIXTURE AT 5000 FT

CRUISE PERFORMANCE WITH RECOMMENDED LEAN MIXTURE AT 7500 FT

CRUISE PERFORMANCE WITH RECOMMENDED LEAN MIXTURE AT 10,000 FT

CRUISE PERFORMANCE WITH RECOMMENDED LEAN MIXTURE AT 15,000 FT

RANGE PROFILE

LANDING PERFORMANCE

AUXILIARY FUEL SYSTEM

OXYGEN SYSTEM

OXYGEN SYSTEM OPERATION

DEICE BOOT SYSTEM

PROPELLER DEICE SYSTEM

DUAL HEATED PITOT STATIC SYSTEM

ALCOHOL WINDSHIELD DEICE SYSTEM

ECONOMY MIXTURE INDICATOR

AIR CONDITIONING SYSTEM

FIRE DETECTION AND EXTINGUISHING SYSTEM

ANGLE OF ATTACK SYSTEM

Cessna 310 1975 Specifications

General

Manufacturer	Cessna
Model	310
Year	1975
Length	27 ft 2 in
Wingspan	35 ft 6 in
Height	8 ft 11 in
Max Takeoff Weight	5, 500 lb (2, 495 kg)
Range	1, 200 nautical miles
Engine Type	Continental IO-470-U
Number of Engines	2
Empty Weight	3, 150 lbs
Fuel Capacity	65 gallons
Maximum Speed	200 knots
Rate of Climb	1, 200 ft/min
Service Ceiling	20, 000 ft (6, 100 m)
Seating	6
Seating Capacity	6
Category	Light twin-engine aircraft
Horsepower per Engine	285 hp
Cruising Speed	180 knots
Horsepower	285 hp
Type	Twin-engine light aircraft