| CONFIGURATION |
|
Low wing, metal construction,
pressurized cabin, certified to FAR Part 23 amendment 34 (type certificate
A60EU) Single
pilot IFR, authorized in known icing conditions |
| DIMENSIONS |
| Overall length: |
34.92 ft (10.645 m) |
| Height: |
14.29 ft (4.355 m) |
| Wing span: |
41.6 ft (12.68 m) |
| Horizontal tail span: |
16.36 ft (4.988 m) |
| Cabin length: |
13.29 ft (4.050 m) |
| Cabin width: |
3.97 ft (1.210 m) |
| Maximum cabin height: |
4.00 ft (1.220 m) |
| Wing area: |
193.75 sq.ft (18.00 m2) |
|
| POWER PLANT |
| Manufacturer: |
Pratt & Whitney Canada |
| Type: |
Free turbine, inverse flow PT6A-64 |
| Thermodynamic power: |
1,580 ESHP |
| Flat rated power: |
700 SHP |
| Air intake: |
Foreign Object Damage (FOD)
Protection with inertial separator |
|
| PROPELLER |
| Manufacturer: |
Hartzell |
| Model: |
HC-E4N-3/E9083S (K) |
| Diameter: |
91 in (2.31 m) |
| Type: |
All metal, four blade, hydraulic,
constant speed, reverse control and automatic full feathering |
| Governor: |
Woodward 8210.007 |
|
| FUEL |
| Types: |
Jet A, A1, B (ASTM-D1655), JP4,
JP5 (MIL-T-5624L), JP8 (MIL-T-83133A) |
| Total tank capacity: |
290 US gal (1,100 l) |
| Usable fuel: |
282 US gal (1,066 l) |
|
| OIL |
| Type: |
MIL-L-23699C (Viscosity 5 cSt) |
| Total oil capacity: |
12.7 US quarts (12 l) |
| Maximum Consumption: |
0.3 US quart (0.29 l/h) |
|
| OPERATIONAL CHARACTERISTICS |
| Maximum freight volume in cabin: |
123.6 cu.ft (3.5 m3 ) |
| Freight floor area: |
33.9 sq.ft (3.15 m2) |
| Cargo door dimensions: |
3.9 ft x 3.54ft (1.19 m x 1.08 m) |
| Optional pilot door dimensions: |
3.34 ft x 2.56 ft (1.02 m x 0.78
m) |
|
| LOADING |
| Operating empty weight: |
4,100 lbs (1,860 kg) |
| Maximum take-off weight: |
6,579 lbs (2,984 kg) |
| Maximum ramp weight: |
6,614 lbs (3,000 kg) |
| Maximum landing weight: |
6,250 lbs (2,835 kg) |
| Useful load: |
2,514 lbs (1,140 kg) |
|
Max payload
(refer to payload / range diagram)
|
1,764 lbs (800 kg) |
|
Luggage compartments:
|
| Aft (pressurized): |
220 lbs (100 kg) |
Fwd (unpressurized) Load:
Door:
|
110 lbs (50 kg)
1.21 ft x 1.67
ft (0.37 m x 0.51 m) |
|
| PERFORMANCE (ISA) |
| Time to climb to (maximum weight): |
20,000 ft: 11 mn 45 s
30,000 ft: 20 mn 30 s |
| Maximum cruise speed at 26,000 ft: |
300 KTAS (555 km / h) |
| Maximum cruise speed at 30,000 ft: |
243 KTAS (450 km / h) |
| Certified ceiling: |
30,000 ft |
|
| DISTANCE (ISA - 50 ft) |
| Take-off: |
2,133 ft (650 m) |
| Landing: |
2,133 ft (650 m)
with reverse 1,640 ft (500 m) |
|
| RANGE (ISA - 45
nm reserve) |
| Full fuel: |
| Maximum cruise: |
1,350 NM (2,500 km) |
| Economical cruise: |
1,550 NM (2,870 km) |
| 6 pax + luggage (29 lbs per
pax): |
| Maximum cruise: |
900 NM (1,667 km) |
| Economical cruise: |
1,080 NM (2,000 km) |
|
| SYSTEMS |
| Flight controls: |
- Ailerons and spoilers, actuated by push / pull rods and cables
- Conventional empennage with movable part actuated by push / pull rods
- Electrical trim on the three control surfaces
- Slotted flaps with electrical actuation
- Autopilot and vertical speed / altitude preselector
|
|
| Landing gear: |
- Retractable gear with hydraulic actuators
- Emergency actuation with manual hydraulic pump
- Steerable front wheel
- Hydro-pneumatic shock absorbers
- Hydraulic brakes with discs
|
|
| Fuel system: |
- One structural fuel tank per wing
- Engine driven mechanical fuel pump
- Emergency electrical fuel pump
- Automatic or manual fuel tank selector with sequencer unit
- Capacitive fuel gauge system
|
|
| Electric generation and
distribution: |
- Starter generator 56 kW - 28 V
- Auxiliary alternator
- NiCad battery (40A.h)
- NATO external electrical power plug
- Bus Distribution
|
|
| Air conditioning and
pressurization: |
- Environmental Control System (ECS) provided by engine bleed air and bootstrap system
- Pressurization with two regulation valves [p max = 6.2 psi (427 mb)]
- Cabin altitude below 8,000 ft (2,440 m) up to aircraft altitude of 28,500 ft (8,690 m)
|
|
| Emergency oxygen: |
- 3 bottles located under the seats
- Passenger masks
- 2 masks with microphone on front seats
|
|
| Deicing: |
- Pneumatic deicing of wings and impinges leading edges
- Electrical deicing of windshield
- Electrically heated pitots
- Electrical deicing of propeller
- Engine air intake deiced by exhaust gases
|
|
| Specific equipment: |
- Metal reinforced floor (option)
- Tie-down points in floor rails customized according to type of freight
- Pilot door (option)
|
|
| Conversion from freight
configuration to 6 / 7 passengers configuration available for cross-country flying with a
quick-change capability. |
|
| All Socata aircraft fleet are
designed with low maintenance cost in mind. The direct operating cost for the TBM aircraft
is also less expensive than those of the competitors and offers an unequalled
price-to-performance ratio much appreciated by the users. |
