Vertipedia - Airbus Helicopters H225/EC225/EC225e Super Puma Mk II+

Designation format taken from Airbus Helicopters website (i.e. EC225 not EC 225). Sometimes referred to as Super Puma LP

Overview

Data on design, manufacture and status

Design authority: Airbus Helicopters

Primary manufacturer: Airbus Helicopters

Parent type: Airbus Helicopters H225/EC225/AS332

Aircraft status: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift devices: 1 Single main rotor

Dedicated control device: 1 Tail rotor

Crew required: 1 in Side-by-side arrangement

Landing gear: Wheels (all retractable)

Key Characteristics

Data on key physical features

Aircraft Details

Data on aircraft configuration, weights, flight performance and equipment

Layout and Dimensions

Weights and Performance

Engine Details

Primary Lift Device

Primary Control Device

Overall Dimensions
Overall Height:	4.97 m	16.3 ft
Overall Length:	19.50 m	64.0 ft
Overall Width:	16.20 m	53.1 ft

Airframe Dimensions
Airframe Length:	16.79 m	55.1 ft
Airframe Width:	2.00 m	6.6 ft
Airframe Height:	4.60 m	15.1 ft

Landing Gear Dimensions
Landing Gear Base:	5.25 m	17.2 ft
Landing Gear Track:	3.00 m	9.8 ft

Cabin Dimensions
Cabin Internal Height:	1.46 m	4.8 ft
Cabin Internal Length:	7.87 m	25.8 ft
Cabin Internal Width:	1.80 m	5.9 ft

https://www.airbushelicopters.com/site/en/ref/Characteristics_117.html Max Range(no reserve) Standard tanks=838 km Max endurance(no reserve) Standard tanks = 4Hr05Min

Weights
Max Gross Weight (ground):	11,000 kg	24,251 lb
Max Gross Weight (airborne):	11,200 kg	24,692 lb
Max Take-off Weight:	11,000 kg	24,251 lb
Empty Weight:	5,594 kg	12,333 lb

Climb Performance
Max Rate of Climb:	5 m/s	1,063 fpm

Hover Performance
Hover Ceiling IGE:	1,935 m	6,348 ft
Hover Ceiling OGE:	792 m	2,598 ft

Limitations
Max Level Flight Speed:	262 km/h	141 kts
Never Exceed Speed:	324 km/h	175 kts
Service Ceiling:	6,095 m	19,997 ft

Range and Endurance
Max Range:	1,135 km	613 nm
Max Endurance:	6 hrs

Provided powerplant data is for uninstalled, sea level, static operations.

Powerplant
Number of engines:	2
Designation:	Turbomeca Makila 2A1 turbine
Manufacturer:	Turbomeca

Normal Ratings
Max continuous:
Take-off / rated:
Intermediate:
Maximum:

OEI Ratings
OEI contingency:
OEI continuous:
OEI 30-second:	1776 kW	2381 hp
OEI intermediate:

Main Rotor Characteristics
Diameter:	16.20 m	53.15 ft
RPM:	260.5 rpm	260.5 rpm
Direction of Rotation:	Unknown
Hub Type:

Main Rotor Blade Characteristics
Blade Construction:
Blade Chord:
Blade Tip Geometry:
Blade Twist:
Number of Blades:	5

Main Rotor Derived Characteristics
Disc Area:	206.12 m²	2218.7 ft²
Disc Loading:	53.37 kg/m²	10.930 lb/ft²
Solidity:

Main Rotor Blade Derived Characteristics
Blade area per blade:
Tip Speed:	220.96 m/s	724.9 fps

Tail Rotor Characteristics
Diameter:	3.15 m	10.33 ft
Configuration:	Unknown
Direction of Rotation:	Top blade aft
RPM:

Tail Rotor Blade Characteristics
Number of Blades:	4
Blade Construction:
Blade Chord:
Blade Twist:

Tail Rotor Derived Characteristics
Disc Area:	7.79 m²	83.9 ft²
Solidity:

Tail Rotor Blade Derived Characteristics
Tip Speed:
Blade Area (per blade):

References

References and sources used

Airbus H225 Technical Data 2016

Airbus Helicopters
Airbus Helicopters, 09/24/2018
Report or Technical Manual

Related VFS Resources

Resources related to the H225/EC225/EC225e Super Puma Mk II+, provided by the Vertical Flight Society.

Forum Proceedings

Vertiflite articles

Enter a search term in the box above.

Web files from vtol.org

Enter a search term in the box above.

Webpages from vtol.org

Enter a search term in the box above.

Images from the VFS Gallery

Enter a search term in the box above.

Refine / filter your search or find more resources

Related Public Resources

Resources related to the H225/EC225/EC225e Super Puma Mk II+, provided by public sources across the internet.

Publicly-funded resources provided by the US Government

Search at NASA Technical Reports Server (NTRS).

Search at Defense Technical Information Center (DTIC).

Search at SciTech Connect (OSTI).

Public resources provided by select scholarly and academic sources

Search at European Rotorcraft Forum Document Repository.

Search at IOPScience.

Search at CiteSeerX.

Additional links

Search for at Google Scholar.

Search for at Bielefeld Academic Search Engine (BASE).

Search for at Semantic Scholar.

Search for at CORE (COnnecting REpositories).

Search for at JSTOR.

Images

Overview

Attribution

Main Rotor Diameter:	16.20 m	53.15 ft
Max Gross Weight (ground):	11,000 kg	24,251 lb

Number of engines:	2 Turbines
Max Level Flight Speed:	262 km/h	141 kts
Max Range:	1,135 km	613 nm
Max Endurance:	6 hrs	6 hrs