TAKE OFF PERFORMANCE

ITEM

AMBIENT CONDITIONS

DC3/C47-65ARTP

Maximum Weight at Take Off Climb Weight Limit

ISA SL

29000 lbs

+30°C @ SL

28500 lbs

+20°C @ 4000 ft

26300 lbs

Take Off Brake Energy Weight Limit

Special Note: The DC3/C47-65ARTP does not have a Take off Brake Energy Weight Limitation.

ISA SL

N/A

+30°C @ SL

N/A

+20°C @ 4000 ft

N/A

Take Off Distance to 35 ft, at Maximum Take Off Climb Weight Limit

ISA SL

4500 ft

+30°C @ SL

4800 ft

+20°C @ 4000 ft

5200 ft

Accelerate/Stop Distance, at Maximum Take Off Climb Weight Limit

ISA SL

4500 ft

+30°C @ SL

4200 ft

+20°C @ 4000 ft

4400 ft

LANDING PERFORMANCE

Landing Distance (Over 50 ft Obstacle)

ISA SL

3200 ft

+30°C @ SL

3450 ft

+20°C @ 4000 ft

3400 ft

AIRSPEED LIMITATIONS

ITEM

AMBIENT CONDITIONS

DC3/C47-65ARTP

V_MO  (Maximum Operating)

170 KIAS

V_A  (Manoeuvring)

107 KIAS

V_LO  (Landing Gear Operating)

141 KIAS

V_LE  (Landing Gear Extended)

141 KIAS

V_FE  (Flap Extended ¼ )

133 KIAS

V_FE  (Flap Extended ½ )

97 KIAS

V_FE  (Flap Extended ¾ to Full)

95 KIAS

Maximum Demonstrated Cross Wind Component

13 Kts

Maximum Tail Wind Component

10 Kts

V_MCA  (Minimum Control Speed Air)

67 KIAS

V_MCG  (Minimum Control Speed Ground)

60 KIAS

WEIGHT LIMITATIONS

Maximum Ramp Weight

29300 lbs

Maximum Take Off Weight

29000 lbs

Maximum Landing Weight

28750 lbs

Maximum Zero Fuel Weight

26200 lbs

FUEL QUANTITY

Total Fuel Quantity (Standard)

7006 lbs

Useable Fuel Quantity (Standard)

6932 lbs

Total Fuel Quantity (Standard + Optional Wing Tanks)

12092 lbs

Useable Fuel Quantity (Standard + Optional Wing Tanks)

12004 lbs

MISCELLANEOUS

Center Of Gravity Range

13 % to 28 % MAC

Maximum Certified Altitude

24000 ft

Minimum Crew

2 (pilot and co pilot)

Noise Characteristics

No acoustical change was shown under provisions of FAR 21.93 (b)

Operating Temperature Limits

-40°C to ISA +35°C

ENGINES

Make and Model

Pratt and Whitney Canada, PT6A-65AR

Take Off Power

1424 SHP up to 82°F
SFC:- 0.509 lb/SHP/hr

Alternate Take Off Power

1230 SHP up to 84°F
SFC:- 0.521 lb/SHP/hr

Maximum Continuous Power

1165 SHP up to 101° F
SFC:- 0.522 lb/SHP/hr

Maximum Climb and Cruise Power

956 SHP up to 85° F
SFC:- 0.552 lb/SHP/hr

Engine Dry Weight

486 lbs

PROPELLERS

Make and Model

Hartzell
HC-B5MP-3C/M10876

FUSELAGE EXTENSION

Fuselage extension length

40 inch

WINGS

Centre wing re-inforcement

Incorporated

Wing tips

Modified wing tips

HYDRAULIC SYSTEM

Engine driven pumps

Gear type engine driven pumps, continuous operation, hydraulic pressure unloading accomplished by standard Douglas hydraulic pressure regulator

FLIGHT CONTROL SYSTEM

Control Surfaces (See Note 2)

Covered with Ceconite 101

Stability Augmentation System

Electronically controlled Stability augmentation servo and tension spring

ELECTRICAL SYSTEM

Starter/Generators

250 Amp

Batteries

Two 38 A/H 28 Volt Batteries

Electrical Distribution System

Nine bus system with Essential and Emergency Busses and crew selected bus tie capability

DE-ICING EQUIPMENT

Engine intake

Full de-icing system installed

Propellers

Full de-icing system installed

Pitot Heaters

Anti-icing system installed

Wing and empennage de-icing

System optional.  Bleed air can be supplied from engine.

FUEL SYSTEM

Additional fuel tanks (Standard Configuration)

Two Main fuel tanks installed, 125 US Gallons each

Fuel quantity indication system

Capacitance Probes and indicators

Transfer pumps

Four electrically driven

Transfer pump interconnection system

Interconnection system installed to provide fuel transfer capability with a single operable transfer pump.

Fuel booster pumps

Four electrically driven

ENGINE FIRE EXTINGUISHER SYSTEM

Number of fire extinguishers

Four, two per engine

WHEEL BRAKES

Type of Wheel Brakes installed

Goodyear single floating disc brakes