TANGARA(TB 360)

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Missions
  • Advance instrument training
  • Twin-engine transformation
  • Cross-country aircraft
Specifications
The Tangara is a 4 place, retractable gear, twin-engine aircraft with a constant speed propeller designed for use in normal
category
Configuration Low wing, metal construction, FAR Part 23 amendments 1 through 16 certified (French Type certificate n 165) for VFR or IFR operations (subject to equipment)
Seating 

- Front seats : ...........................................2

- Rear  seats : ...........................................2
Dimensions 

- Overall length : .........................29.8 ft (9.09 m)

- Height :...........................10 ft 4 1/4 in (3.16 m)
- Wing span :......................36 ft 10 1/4 in (11.23 m)

- Horizontal tail span :................13 ft 11 in (4.24 m)

- Wing area :...........................184 sq.ft (17.09 m2)

- Cabin length :..........................9 ft 6 in (2.90 m)

- Cabin width :...........................3 ft 9 in (1.14 m)

- Max. cabin height :.....................4 ft 1 in (1.25 m)

- Wheelbase :.............................6 ft 8 in (2.03 m)
Engine 

- Manufacturer : ..................................Lycoming

- Type : .............................O-320-D1D 4 cylinders

- Power rating : ...................................160 BHP

- Recommended TBO : ............................2,000 hours
Propeller 

- Manufacturer : ..................................Hartzell

- Diameter : ................................73 in (1.85 m)

- Blades : ...............................................2

- Type : ....................Constant speed with feathering
Fuel 

- Type : ............................................100 LL

- Total tank capacity : .................118 US gal (447 l)

- Usable fuel : .......................114 US gal (431.5 l)
Oil 

- Tank capacity : ......................8 US quarts (7.6 l)
Systems - Flight controls :
  • Dual yoke controls
  • Push pull rods and cables
  • Manual trim actuated by cables
  • Electrically actuated flaps

- Landing gear :

  • Retractable tricycle landing gear

- Fuel System :

  • One structural fuel tank per wing and a feeder tank
  • Two engine driven fuel pumps
  • Two electric auxiliary fuel pumps

- Electrical Systems :

  • Battery 24 V/36 A/h
  • Two alternators 28 V/70 A
  • Two voltage regulators
  • Circuit-breakers
  • Bendix King Avionics
additional Benefits - Bonded metal structure
Loading 

- Average empty weight : ..............2,588 lbs (1,174 kg)

- Max. take-off weight : ..............3,800 lbs (1,724 kg)

- Max. landing weight : ...............3,800 lbs (1,724 kg)

- Max. useful load : ....................1,212 lbs (550 kg)

- Max. weight in luggage compartment : ....250 lbs (113 kg)
Performance 

- Climb rate at Z = 0 : ..............1,400 ft/mn (7.1 m/s) 

- Single engine

  Climb rate at Z = 0 : ..................310 ft/mn (1.6 m/s)

- Cruise speed :

Max. at 0 ft.......................174 KTAS (322 km/h)

at 75% at 8,500 ft.................165 KTAS (306 km/h)

at 45% at 8,500 ft.................120 KTAS (222 km/h)

- Crosswind component :...............................15 kt

- Certified ceiling :.............................20,000 ft

- Single engine certified ceiling :.................5,500 ft

- Take-off - clear 50 feet :...............1,670 ft (509 m)

- Landing - clear 50 feet :................1,330 ft (405 m)

- range at 8,500 ft with full tanks :

at 75% power.........................800 NM (1,480 km)

at 45% power.......................1,140 NM (2,110 km)