Augusta 109

The A109 Power light multi-role helicopter has been developed by AgustaWestland in Italy. The A109 is built in civil and military versions. The civil family of A109 helicopters includes the A109K2 civil rescue helicopter used by the Swiss rescue service, the A109K2 police helicopter and the A109 Power civil multi-role helicopter. The A109 was originally developed as an ambulance and rescue helicopter to operate in the mountainous regions of Switzerland. The helicopter can fly from critically situated landing spots in adverse climates and from roof helipads in densely populated areas.

The A109 Power first flew in 1995 and entered service in 1997. Over 300 have been ordered for police, EMS (emergency medical), VIP/Corporate and military applications.

Recent orders include three for the 32 (Royal Squadron) of the UK Royal Air Force, ordered in May 2005. The helicopters will be used for VIP transport and communications and will be delivered from 2006. The Japanese National Police Agency placed an order for three additional A109 Powers in June 2005.

An armed version, the MH-68A Stingray, is in service with the US Coastguard's Helicopter Tactical Squadron (HITRON) for drug interdiction. Utility versions have been ordered by the South African Air Force and the Swedish Army.

The A109E Power helicopter can be configured as a passenger helicopter for four or six passengers. The cabin can be quickly converted for an emergency medical evacuation role. It can be fitted with four seats for medical attendants and a litter for a single stretcher patient. A second litter can be stowed in the baggage compartment to the rear of the main cabin.

The helicopters have high engine power, FADEC management, composite rotor head and blades, advanced avionics and cockpit integration providing high performance in terms of speed, range and mission effectiveness.

The latest variant is the A109S Grand, a stretched version, which has a maximum take-off weight of 3,175kg and cabin length of 2.3m. First deliveries of the A109S Grand were in June 2005

A109 DESIGN

The helicopter airframe consists of a lightweight aluminium alloy and honeycomb structure with high crashworthiness. Two large sliding doors provide easy access and cargo operation and are in-flight operable. There are two separate pilot's doors. The long tailboom configuration provides high yaw control for operation in strong winds.

The tricycle-type wheeled landing gear is fitted with air and oil shock absorbers for ground mobility and operation on rough terrain. Energy absorbing struts provide increased crashworthiness. A swivelling forward wheel gives easy ground manoeuvrability.

The four-bladed fully articulated main rotor has low vibration, low flicker and reduced noise level characteristics. The main rotor head is made of titanium with composite elastomeric bearings and blade grips. The composite main rotor blades are ballistic tolerant for high survivability and reliability. The rotor is negative-g capable for high manoeuvrability. The tail rotor is a two-bladed stainless steel semi-rigid type.

COCKPIT

The helicopter is equipped with an ergonomically designed glass cockpit with provision for mission dedicated displays and control instrumentation. The A109 Power has single and dual pilot IFR (Instrument Flight Rules) capability with a three-axis duplex automatic flight control system (AFCS).

The helicopter can be fitted with either Rockwell Collins ProLine II or Honeywell Silver Crown avionics suite. The navigation systems include an automatic direction finding navigation aid (ADF), distance measuring equipment (DME), a global positioning system (GPS), a radar altimeter, an emergency locator transponder (ELT), a VHF omnidirectional radio ranger (VOR), ground speed meter and inertial location system.

The flight control system includes a collective, cyclic and anti-torque system. The cyclic and collective controls are powered by two hydraulic systems. The anti-torque control system is hydraulically powered. A dual redundant three-axis stability augmentation system is fitted as an option.

An optional Rockwell Collins Cockpit Management System is provided for monitoring and operating different avionics via one or more centrally located control and display units.

ENGINES

The helicopter is powered by two side-by-side Pratt & Whitney PW-206C or Turbomeca Arrius 2K1 engines with Full Authority Digital Electronic Control (FADEC). Each engine is equipped with independent fuel and oil systems and independent engine controls.

The transmission system is rated at 900hp for improved high temperature and high altitude performance. For enhanced safety and reliability the helicopter has a 640hp single engine emergency rating and the dry run capability is 30 minutes allowing the pilot the opportunity to find a safe landing spot in the event of oil loss.

FUEL SYSTEM

There are three fuel systems configurations: three cells of 605 litres, four cells of 710 litres and five cells of 870 litres. A crashworthy fuel system, with closed circuit refuelling and self-sealing fuel tanks can be fitted as an option.

HYDRAULIC SYSTEM

The helicopter is fitted with two independent flight control hydraulic systems, each capable of operating main actuators in case of failure of the other system. The utility hydraulic system has two accumulators (a normal and an emergency accumulator) to operate the rotor brake, the wheel brakes and the nose wheel centring device.