Beechcraft Duke A60

A four to six place, twin engine, high performance, turbocharged, pressurized monoplane with fully retractable tricycle landing gear. Standard equipment includes avionics and a full complement of engine and flight instruments. Licensed in normal category. Designed and tested in excess of required load factors.

PERFORMANCE

 

CRUISING SPEEDS (Averages cruise weight) with Optional 202 gal. fuel capacity

79% Power

25,000 ft……………………………………….. 278 mph (242 kts)

20,000 ft……………………………………….. 265 mph (230 kts)

15,000 ft……………………………………….. 252 mph (219 kts)

75% Power

25,000 ft………………………………………. 272 mph (236 kts)

20,000 ft……………………………………….. 259 mph (225 kts)

15,000 ft……………………………………….. 247 mph (215 kts)

65% Power

25,000 ft………………………………………. 278 mph (242 kts)

20,000 ft……………………………………….. 265 mph (230 kts)

15,000 ft……………………………………….. 252 mph (219 kts)

45% Power

25,000 ft……………………………………….. 278 mph (242 kts)

20,000 ft……………………………………….. 265 mph (230 kts)

15,000 ft……………………………………….. 252 mph (219 kts)

HIGH SPEED

(At 23,000 ft.)……………………………….. 286 mph (248 kts)

STALL SPEED – 6,775 lbs

Power Off, flaps down, gear down…….. 67 mph (76 kts.)

RANGE

75% Power

25,000 ft…………………………………………. 963 mi (837 nm)

20,000 ft…………………………………………. 950 mi (825 nm)

15,000 ft…………………………………………. 931 mi (809 nm)

65% Power

25,000 ft………………………………………. 1,077 mi (936 nm)

20,000 ft………………………………………. 1,058 mi (919 nm)

15,000 ft………………………………………. 1,040 mi (904 nm)

45% Power

25,000 ft………………………………………. 1,077 mi (936 nm)

20,000 ft………………………………………. 1,058 mi (919 nm)

15,000 ft………………………………………. 1,040 mi (904 nm)

Range includes allowances for warm-up, taxi, take-off, climb, and 45-minute reserve at 45% power.

RATE OF CLIMB AT SEA LEVEL

Two engines – 6,775 lbs……………………………………… 1,601 fpm

Two engines – 6,000 lbs……………………………………… 1,930 fpm

Two engines – 5,200 lbs……………………………………… 2,373 fpm

Single engine – 6,775 lbs………………………………………. 307 fpm

Single engine – 6,000 lbs………………………………………. 496 fpm

Single engine – 5,200 lbs………………………………………. 739 fpm

SERVICE CEILING

Two engines (100 fpm) – 6,775 lbs……………………….. 30,800 ft

Two engines (100 fpm) – 6,000 lbs……………………….. 33,400 ft

Two engines (100 fpm) – 5,200 lbs……………………….. 35,800 ft

Single engine (50 fpm) – 6,775 lbs………………………… 15,100 ft

Single engine (50 fpm) – 6,000 lbs………………………… 20,200 ft

Single engine (50 fpm) – 5,200 lbs………………………… 23,800 ft

NORMAL TAKE-OFF DISTANCE – 6,775 lbs.

Ground roll……………………………………………………………. 2,006 ft

Total Distance over 50 ft. obstacle………………………….. 2,626 ft

NORMAL LANDING DISTANCE – 6,775 lbs. (30° Flaps)

Ground roll……………………………………………………………. 1,318 ft

Total Distance over 50 ft. obstacle………………………….. 3,065 ft

The above performance figures are based on maximum gross weights and are the results of flights tests of the Duke A60 conducted by Beech Aircraft Corporation under factory-controlled conditions and will vary with individual aircraft and numerous factors affecting flight performance.

 

SPECIFICATIONS

 

WEIGHTS

Ramp Weight…………………………………………………….. 6,819 lbs.

Gross Weight (Take-off and landing)……………………. 6,775 lbs.

Empty Weight (Approx.)………………………………………. 4,195 lbs.

(Empty weight includes complete set of flight instruments, cabin heating and ventilating system with windshield defrosting, soundproofing, night flying equipment and standard avionics)

Useful Load………………………………………………………… 2,580 lbs.

(includes 24 lbs of unusable fuel and oil)

DIMENSIONS

Wing Span………………………………………………………… 39 ft. 3 in.

Length…………………………………………………………….. 33 ft. 10 in.

Height………………………………………………………………. 12 ft. 4 in.

Cabin Length, inside………………………………………………… 142 in.

Cabin Width, inside…………………………………………………… 50 in.

Cabin Door Opening…………………. 47 1/2 in. high x 26 1/2 in. wide

Nose Baggage Door Opening…….. 23 1/2 in. high x 37 1/2 in. wide

Cabin Height, Inside………………………………………………….. 52 in.

WING AREA AND LOADING

Wing Area………………………………………………………. 212.9 sq. ft.

Wing Loading at Gross Weight……………………… 31.8 lbs/sq. ft.

Power Loading at Gross Weight………………………….. 8.9 lbs/hp.

PRESSURIZATION

(4.6 Differential) Cabin Altitude

Actual Aircraft Altitude – 10,100 ft……………………….. Sea Level

Actual Aircraft Altitude – 21,600 ft…………………………. 8,000 ft.

Actual Aircraft Altitude – 24,800 ft……………………….. 10,000 ft.

FUEL AND OIL CAPACITY

Standard Fuel………………………………………………….. 142 gallons

Optional Fuel…………………………………………………… 202 gallons

Oil Capacity……………………………………………………… 6 1/2 gallons

BAGGAGE

*Front Baggage Compartment, size………………………. 32 cu. ft.

Rear Baggage Area, size (4 or 6 seats)………………… 28 1/4 cu ft.

*Front Baggage Compartment

(Weight Limit 45 lbs/sq ft)………………………………. 500 lbs.

Rear Baggage Limits……………………………………………… 315 lbs.

 

*Includes 6.5 cubic feet for Standard Avionics

FONTE:www.dukeflyers.org/