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AIRBUS HELICOPTERS H225 Super Puma Mk II+
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EC25
| Aircraft | ||||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Name | H225 Super Puma Mk II+ | |||||||||||||
| Manufacturer | AIRBUS HELICOPTERS | |||||||||||||
| Body | Narrow | |||||||||||||
| Wing | Rotary | |||||||||||||
| WTC | Medium | |||||||||||||
| APC | A | |||||||||||||
| Type code | H2T | |||||||||||||
| Engine | Turboshaft | |||||||||||||
| Engine count | Multi | |||||||||||||
| Mass group | 3 | |||||||||||||
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AIRBUS HELICOPTERS H225 Super Puma Mk II+
Description
The The Airbus Helicopters H225 Super Puma Mk II+ is a long-range passenger transport helicopter developed as the next generation in the civilian Super Puma family. It is a twin-engined aircraft and can carry up to 24 passengers along with 2 crew and a cabin attendant, dependent on customer configuration. The helicopter is marketed for offshore support and VIP passenger transport duties, as well as public service missions.
The H225 (and EC-225) is based on the Eurocopter AS332L2 Super Puma, improving upon the design with a five-blade main rotor incorporating a new airfoil shape to reduce vibration levels. The helicopter is powered by two Turbomeca Makila 2A1 turboshaft engines mounted over the cabin, which feature a dual-channel Full Authority Digital Engine Control (FADEC) system and anti-icing system to enable it to operate in very cold climates. Other improvements include a reinforced main rotor gearbox and a full glass cockpit with Active Matrix Liquid Crystal Displays.
Technical Data
| Wing span | 16.2 m53.15 ft <br /> |
|---|---|
| Length | 19.5 m63.976 ft <br /> |
| Height | 4.97 m16.306 ft <br /> |
| Powerplant | 2 x Turboméca Makila 2A1 turboshaft engines, 1,776 kW (2,382 hp) each |
| Engine model | Turboméca Makila |
Performance Data
| Take-Off | Initial Climb (to 5000 ft) |
Initial Climb (to FL150) |
Initial Climb (to FL240) |
MACH Climb | Cruise | Initial Descent (to FL240) |
Descent (to FL100) |
Descent (FL100 & below) |
Approach | ||||||||||
| V2 (IAS) | kts | IAS | kts | IAS | kts | IAS | kts | MACH | TAS | 130 kts | MACH | IAS | kts | IAS | kts | Vapp (IAS) | kts | ||
| Distance | m | ROC | ft/min | ROC | ft/min | ROC | ft/min | ROC | ft/min | MACH | ROD | ft/min | ROD | ft/min | MCS | kts | Distance | m | |
| MTOW | 1120011,200 kg <br />11.2 tonnes <br /> kg | Ceiling | FL200 | ROD | ft/min | APC | A | ||||||||||||
| WTC | M | Range | 250250 nm <br />463,000 m <br />463 km <br />1,519,028.873 ft <br /> NM | ||||||||||||||||
Accidents & Serious Incidents involving EC25
- EC25, en-route, 20nm east of Aberdeen UK, 2012 (On 10 May 2012, the crew of a Eurocopter EC225 LP on a flight from Aberdeen to an offshore platform received an indication that the main gearbox (MGB) lubrication system had failed. Shortly after selecting the emergency lubrication system, that also indicated failure and the crew responded in accordance with the QRH drill to “land immediately” by carrying out a successful controlled ditching. The ongoing investigation has found that there had been a mechanical failure of the MGB but that the emergency lubrication system had, contrary to indications, been functioning normally.)
- EC25, en-route, 32nm southwest of Sumburgh UK, 2012 (On 22 October 2012, the crew of a Eurocopter EC225 LP on a flight from Aberdeen to an offshore platform received an indication that the main gearbox (MGB) lubrication system had failed. Shortly after selecting the emergency lubrication system, that system also indicated failure and the crew responded in accordance with the QRH drill to “land immediately” by carrying out a successful controlled ditching. The ongoing investigation has found that there had been a mechanical failure within the MGB but that the emergency lubrication system had, contrary to indications, been functioning normally.)
- EC25, vicinity Bergen Norway, 2016 (On 29 April 2016, an Airbus EC225 Super Puma main rotor detached without warning en-route to Bergen. Control was lost and it crashed and was destroyed. Rotor detachment was attributed to undetected development of metal fatigue in the same gearbox component which caused an identical 2009 accident to a variant of the same helicopter type. Despite this previous accident, the failure mode involved had not been properly understood or anticipated. The investigation identifies significant lessons to be learned related to gearbox design, risk assessment, fatigue evaluation, gearbox condition monitoring, type certification and continued airworthiness, which may also be valid for other helicopter types.)
- EC25, vicinity ETAP Central offshore platform, North Sea UK (On 18 February 2009, the crew of Eurocopter EC225 LP Super Puma attempting to make an approach to a North Sea offshore platform in poor visibility at night lost meaningful visual reference and a sea impact followed. All occupants escaped from the helicopter and were subsequently rescued. The investigation concluded that the accident probably occurred because of the effects of oculogravic and somatogravic illusions combined with both pilots being focused on the platform and not monitoring the flight instruments.)
- EC25, Åsgård B Platform North Sea, 2012 (On 12 January 2012, the crew of an EC 225LP helicopter were unable to prevent it almost departing the helideck at the offshore platform where it had just made a normal touch down at night after an en route diversion prompted by a partial hydraulic failure. An emergency evacuation was ordered and ground crew intervention prevented further helicopter movement. A component in the left main landing gear brake unit was found to have failed due to a manufacturing fault. Emergency Regulatory action for the helicopter type followed in respect of both the airworthiness and operational issues highlighted by the Investigation.)