Vertipedia - HAL ALH Dhruv Mark I

The Advanced Light Helicopter Dhruv Mark I configuration included mechanical gauges in the (conventional) cockpit, the TM 333-2B2 engine, an Anti-Resonance Vibration Isolation System (ARIS) and Frahm dampers (developed by LORD Corporation). The fuel capacity, useful load and under slung load are 1055 kg, 2490 kg, and 1500 kg, respectively. Passenger capacity is 12-14 plus the crew.

Overview

Data on design, manufacture and status

Design authority: Hindustan Aeronautics Limited

Primary manufacturer: Hindustan Aeronautics Limited

Parent type: HAL Dhruv

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: 1-2 in Side-by-side arrangement

Landing gear: Skids

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

Composite material air frame.

Overall Dimensions
Overall Height:	4.91 m	16.1 ft
Overall Length:	15.87 m	52.1 ft
Overall Width:	13.20 m	43.3 ft

Airframe Dimensions
Airframe Length:	12.89 m	42.3 ft
Airframe Width:	3.19 m	10.5 ft
Airframe Height:	3.89 m	12.8 ft

Landing Gear Dimensions
Landing Gear Base:
Landing Gear Track:

Cabin Dimensions
Cabin Internal Height:	1.42 m	4.7 ft
Cabin Internal Length:
Cabin Internal Width:	1.97 m	6.5 ft

Weights
Max Gross Weight (ground):	5,500 kg	12,125 lb
Max Gross Weight (airborne):
Max Take-off Weight:	5,500 kg	12,125 lb
Empty Weight:	2,580 kg	5,688 lb

Climb Performance
Max Rate of Climb:	9 m/s	1,772 fpm

Hover Performance
Hover Ceiling IGE:
Hover Ceiling OGE:

Limitations
Max Level Flight Speed:	280 km/h	151 kts
Never Exceed Speed:	305 km/h	165 kts
Service Ceiling:	6,500 m	21,325 ft

Range and Endurance
Max Range:
Max Endurance:

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

Powerplant
Number of engines:	2
Designation:	Turbomeca TM 333 2B2 turbine
Manufacturer:	Turbomeca

Normal Ratings
Max continuous:	736 kW	987 hp
Take-off / rated:	825 kW	1106 hp
Intermediate:
Maximum:

OEI Ratings
OEI contingency:	841 kW	1127 hp
OEI continuous:	807 kW	1082 hp
OEI 30-second:	910 kW	1220 hp
OEI intermediate:	807 kW	1082 hp

Main Rotor Characteristics
Diameter:	13.20 m	43.31 ft
RPM:	314.0 rpm	314.0 rpm
Direction of Rotation:	Clockwise
Hub Type:	Fiberglass elastomeric (FEL)

Main Rotor Blade Characteristics
Blade Construction:	Flexible fibreglass
Blade Chord:	0.500 m	1.64 ft
Blade Tip Geometry:
Blade Twist:
Number of Blades:	4

Main Rotor Derived Characteristics
Disc Area:	136.85 m²	1473.1 ft²
Disc Loading:	40.19 kg/m²	8.232 lb/ft²
Solidity:	0.0965

Main Rotor Blade Derived Characteristics
Blade area per blade:	3.30 m²	35.5 ft²
Tip Speed:	217.02 m/s	712.0 fps

Tail rotor blade form: rectangular, parabolic tip

Tail Rotor Characteristics
Diameter:	2.55 m	8.37 ft
Configuration:	Pusher
Direction of Rotation:	Unknown
RPM:	1564 rpm	1564 rpm

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

Tail Rotor Derived Characteristics
Disc Area:	5.11 m²	55.0 ft²
Solidity:

Tail Rotor Blade Derived Characteristics
Tip Speed:	208.82 m/s	685.1 fps
Blade Area (per blade):

References

References and sources used

Hindustan Aeronautics Limited

Hindustan Aeronautics Limited
14 June 2017
Website

Information Manual, Advanced Light Helicopter

HIndustan Aeronautics Limited
Information Manual Advanced Light Helicopter, circa 1992 (page 8)
Report or Technical Manual
No page numbers in the manual, page numbers marked with very first page being 1.