MSFS 2024 · Rotary
Eurocopter EC135 T1 Quick Reference
V-SPEEDS
| Speed | Value | Description |
|---|---|---|
| Vne | 155 KIAS at MSL | EASA TCDS EASA.R.009 Issue 20, SECTION 10/11 para III.8 for the EC135 T1. Refer to the approved RFM for the reduction in VNE with altitude |
| Vy (best climb) | 65 KIAS | EC135 P2+ FM 4.6 and 3.4.5 - P2+ source, airframe performance figure |
| Vauto (recommended) | 75 KIAS | EC135 P2+ FM 3.4.14 - P2+ source |
| Vauto (max range) | 90 KIAS | EC135 P2+ FM 3.4.14 - P2+ source |
| Vauto (min rate of descent) | 60 KIAS | EC135 P2+ FM 3.4.14 - P2+ source |
| Takeoff segment speed | 50 KIAS to 50 ft AGL | EC135 P2+ FM 4.6, then accelerate to Vy and climb through 100 ft AGL |
| Approach speed | 40 KIAS at 50 ft AGL | EC135 P2+ FM 4.8, descending 300 to 500 ft/min |
| Tail rotor failure fwd flight | 70 KIAS or higher | EC135 P2+ FM 3.6.2 - P2+ source |
POWER SETTINGS
| Phase | Setting |
|---|---|
| Pre-takeoff | Rotor RPM / N2 at or above 97 percent |
| Hover / takeoff | Rotor RPM at or above 100 percent; FLI needles matched at the same parameter |
| AEO takeoff (5 min) | 2 x 75 percent torque, Ng 101.1 percent, power turbine 104 percent, TOT 895 degC |
| AEO max continuous | 2 x 69 percent torque, Ng 98.7 percent, power turbine 104 percent, TOT 855 degC |
| OEI 2.5 min takeoff | 1 x 119.8 percent torque, Ng 103.7 percent, power turbine 104 percent, TOT 945 degC |
| OEI max continuous | 1 x 86 percent torque, Ng 101.1 percent, power turbine 104 percent, TOT 895 degC |
| Autorotation | Collective reduced to maintain rotor RPM within limits, 75 KIAS recommended |
ENGINE LIMITS
| Parameter | Value |
|---|---|
| Engines | 2 x Safran Helicopter Engines (former Turbomeca) Arrius 2B1 / 2B1A / 2B1A_1 |
| AEO-TOP torque (5 min) | 2 x 75 percent |
| AEO-TOP gas generator | 57,706 rpm (101.1 percent) |
| AEO-TOP power turbine | 104 percent |
| AEO-TOP TOT | 895 degC |
| AEO-MCP torque | 2 x 69 percent |
| AEO-MCP gas generator | 53,406 rpm (98.7 percent) |
| AEO-MCP power turbine | 104 percent |
| AEO-MCP TOT | 855 degC |
| OEI-TOP torque (2.5 min) | 1 x 119.8 percent |
| OEI-TOP gas generator | 56,113 rpm (103.7 percent) |
| OEI-TOP TOT | 945 degC |
| OEI-MCP torque | 1 x 86 percent |
| OEI-MCP gas generator | 54,706 rpm (101.1 percent) |
| OEI-MCP TOT | 895 degC |
| Rotor speed power on | 104 percent maximum, 95 percent minimum |
| Rotor speed power off | 106 percent maximum; 80 percent minimum up to 1,900 kg, 85 percent minimum above 1,900 kg |
| Rotor transient limits | Refer to the approved RFM |
KEY NUMBERS
| Parameter | Value |
|---|---|
| Maximum mass | 2,720 kg. Operation to 2,835 kg only per RFMS 9.1-3 with SB EC135-11-003 |
| Max operating altitude | 20,000 ft (6,096 m) pressure altitude |
| Fuel capacity (from s/n 0250) | 710.0 litres, 700.5 litres usable |
| Fuel capacity (up to s/n 0249) | 680.0 litres, 670.5 litres usable |
| Main rotor | Bearingless, 4 blades, 10.20 m diameter |
| Tail rotor | Fenestron, 10 blades, 1.00 m diameter |
| Minimum flight crew | 1 pilot, right seat |
| Maximum passengers | 1 cockpit and 6 cabin, or 7 cabin with the RFMS 9.2-31 kit |
| Passenger emergency exits | 2, one on each side of the passenger cabin |
| Cargo floor max load | 1,130 kg; maximum unit load 600 kg per square metre |
| Lateral CG | Maximum deviation 100 mm right or left |
| Operating limitations | VFR day and night, non-icing conditions |
| Airworthiness category | Small Rotorcraft, certified to JAR 27 Issue 1 |
| Fuselage dimensions | Length 5.87 m, width 1.56 m, height 3.35 m |