LET L-410 UVP-E
REFERENCE INFORMATION
For standard procedures, see the Checklists tab.

LIMITATION OF OPERATING SPEED
Speed designation | Name of the speed | Speed (km/h) IAS
Vmax.max | Design limit speed (calculated) | 400
Vmax. MO | Maximum operating speed | 350
Vmax. FE18 | Max. permissible cruise speed with wing flaps extended to 18° | 250
Vmax. FE42 | Max. permissible cruise speed with wing flaps extended to 42° | 220
Vmax. LO | Maximum permissible landing gear operating speed | 250*
Vmax. Spoil | Maximum permissible spoiler extension speed | 190

* At speed v=205 km/h IAS is extension blocked

###

### Flight performance

Flight performance are valid under following conditions:

- international standard atmosphere
- maximum take-off weight 6 400 kg
- customer bleed is off

#### Both engines are operation

(1) | Real take-off run at speed vR = 150 km/h IAS (161 km/h EAS) | 400 m.
Maximum take-off engine rating, propeller speed | 2080 RPM
take-off configuration flaps | 18°
aerodrome altitude ISA, no wind, concrete runway steep | 0 m

(2) | Real landing run after landing speed of 140 km/h IAS when using wheel brakes and reverse thrust of both engines | 240 m * * Required runway length
Maximum landing weight Is 6200 kg, both engines idle, landing configuration – wing flaps extended to 42°, spoilers. extended before touch-down (as per Flight Manual), airport altitude: 0 m ISA, no wind, concrete runway steep 0, approach speed vapr= 155 km/h IAS (161 km/h EAS) | 800 m (100 m clearway)

(3) | Climb rate |
Maximum continuous engine rating |
Propeller speed | 1900 RPM
cruise configuration (wing flaps and landing gear retracted) |

Flight altitude | Climb time from 400 m circuit in minutes | Torque
500 | 0,3 | < 100
1000 | 1,6 | < 100
2000 | 4,4 | < 100
3000 | 7,7 | < 100
4000 | 12,5 | < 100

(5) | Range
Range value is valid under following conditions:
- 8 main fuel tanks In the wing
- max. take-off weight 6400 kg
- ISA atmospheric conditions, no wind
- two engines operative
- leveled flight block altitude 4200 m
- cruise speed 365 km/h IAS
- climb rate at climbing from 400 m to 4200 m: 3 m/s
- rate at descent from 4200 m to 400 m: 3 m/s
propeller speed 1900 RPM
descent at engine rating cruise speed 310 km/h, propeller speed nprop = 1700 RPM
- range tolerance: 3%
- cruise configuration (wing flaps retracted)

(a) | Range with maximum payload 1615 kg and 625 kg of fuel (without wing tip tanks)
- with fuel reserve for 30 minutes at speed 287 km/h IAS at altitude of 2100 m | 546 km
- with fuel reserve for 45 minutes at speed 287 km/h IAS at altitude of 2100 m | 466 km

(b)
Maximum range without wing tip tanks and payload of 1330 kg and 910 kg of fuel
- with fuel reserve for 30 minutes at speed of 287 km/h IAS at altitude 2 100 m | 298 km

(c)
Maximum range with wing tip tanks with payload of 885 kg and 1300 kg of fuel
- with fuel reserve for 30 minutes at speed 287 km/h IAS at altitude 2100 m | 1380 km

### Flight with one engine in operative

### (1) Climb speed

Intermediate Contingency Power Setting Propeller speed: 2080 RPM

Left engine stopped - feathered propeller, flight speed = 200 km/h IAS (210 km/h EAS), cruise configuration (wing flaps and landing gear retracted)

Flight altitude [m] | Climb time from 400 m circuit in minutes | Torque
500 | 1,0 | < 100
1000 | 6,0 | < 100
2000 | 19,0 | < 100
3000 | 40,3 | < 100

NOTE: This aircraft's real-world reference informations have been NOT modified for Flight Simulator.

FARNAIR Hungary Ltd.