agustawestland aw189 search and rescue -...

AgustaWestland AW189Search & Rescue

AgustaWestland AW189Search and Rescue

Confidence in flight. Worldwide.


Version 2.2 - April 2015


Overview

AgustaWestland AW189 Specification

The AgustaWestland 189 is an 8-tonne class medium twin-engine helicopter

that embodies state-of-the-art technologies and designed to comply with the

latest international regulatory requirements. Certified for single or dual pilot

IFR and VFR in accordance with EASA CS-29.

The rotor system comprises a 5-blade composite main rotor, a tilted 4-blade

composite tail rotor and is powered by two FADEC controlled General Electric

GE CT7-2E1 turboshaft engines. At ISA sea level, each engine has a 5 minute

AEO takeoff rating of 1,983 SHP (1,479 kW) and a 2.5 minute OEI rating of

2,104 SHP (1,569 kW). The AW189 is also equipped with a Microturbo 60 kW

e-APU driving a 25kVA starter/generator for starting and back-up electrical

power.

The main gearbox has a gravity-fed lubrication system with a 50 minute ‘run-

dry’ capability without the need for glycol or oil injection. The main hydraulic

system includes dual independent redundant fluid power generation and

distribution. The auxiliary hydraulic system enables the completion of ‘full and

free’ control checks prior to engine start. A utility system provides hydraulic

power for normal and emergency operation of the landing gear.

The main rotor head and the tilted tail rotor head are fully articulated with

elastomeric bearings and titanium hubs. The overall rotors turning length

(D-value) is 17.6 m (57.74 ft) which compares with figures of 16.65 m (54.63 ft)

for the AW139 and 18.06 m (59.25 ft) for the EC175.

The main cabin is constructed of aluminium alloy for the primary structure

and composite material for the secondary structure elements. The rear

fuselage and tail boom are of composite construction. The AW189 is

equipped with a heavy duty retractable tricycle landing gear for all terrain

operations.


Fuel is contained within two crashworthy tanks located behind the cabin with

frangible self-sealing couplings to prevent ruptures and leakage. In the

extended range configuration (Supplement 22), three additional cells are

located under the floor and ejector pumps transfer their contents into the two

main tanks. Refuelling may be carried out using controlled pressure at a point

on the RH side or by gravity at fillers on both LH and RH sides.

The AW189's advanced Electrical Power Generation and Distribution System

(EPGDS) doubles the typical airborne electrical power generation capacity

for helicopters in this class utilising AC Starting and Generation System

Technology, thus saving weight by combining the functionalities of a main

engine starter motor and generator into one component.

In the SAR role the cabin interior has two rows of four seats; aft-facing at the

front and front-facing at the rear. The backrests of the middle two seats in the

rear row may be folded down to allow access to the equipment stowed in the

rear compartment. Four large jettisonable windows are provided on each side

of the cabin with the most forward pair being of ‘bubble’ design to provide the

rear crew with an excellent external field of view during a search phase.

A comprehensive Environmental Control System (ECS) provides fresh air

ventilation, heating and air conditioning. An illuminated 2.4 m³ (84.7 ft³) rear

compartment with access doors on either side is equipped with a net and

tie-down fittings for equipment stowage and maximum loading flexibility.

Two hinged doors provide easy access to the cockpit from either side. The

cockpit is equipped with four 10" x 8" active matrix LCD integrated 'glass'

displays providing primary flight, navigation, weather radar and systems data.

The large forward and side windows provide an excellent field of view for the

flight crew.

Overview (continued)



The comprehensive avionics suite

includes a 4-axis dual-duplex autopilot

and dual Flight Management System. The

cockpit design also incorporates the latest

in advanced situational awareness

technologies including ground proximity

warning and collision avoidance systems

(HTAWS, TCAS II).

AW189 cockpit layoutwith illustrative displays

Primary Flight Display (PFD) Primary Flight Display (PFD)

Multi-Function Display Multi-Function Display

Integrated Standby Instrument System (ISIS)

Multifunction Control Display Unit (MCDU)

Multifunction Control Display Unit (MCDU)

Overview (continued)



HM COASTGUARD

COASTGUARD RESCUE

General Configuration and Dimensions

5.06 m16.6 ft

2.8 m9.2 ft

3.01 m909 ft

4.79 m15.7 ft

4.04 m13.3 ft

2.255 m7.4 ft

2.9 m9.5 ft

2.55 m8.4 ft

17.57 m57.6 ft

rotors turning

4.00 m13.1 ft

14.60 m / 47.9 ftrotor diameter

14.6 m47.9 ft

Clearance~ 290 mm


HM COASTGUARD

COASTGUARD RESCUE

General Configuration - Compartment Dimensions

2.44 m8.0 ft

2.39 m7.84 ft

3.47 m11.4 ft

1.8 m5.9 ft

HM COASTGUARD

1.4 m4.6 ft

0.815 m2.67 ft

Cabin volume11.2 m³ / 395.5 ft³

Rear compartment volume2.4 m³ / 85 ft³


Leading Particulars

= Normal flight crew . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 pilots + 2 rear crew

= Usable fuel load in the two main fuel tanks . . . . . . . . . . . . 984 kg 2,169 lb

= Usable fuel load in extended range configuration standard tanks plus the 3 underfloor fuel cells . . . . . . . . 2,055 kg 4,530 lb

= Cruise true airspeed . . . . . . . . . . . . . . . . . . . . . . . . 130-150 knots 241-278 km/hr

= Main cabin volume . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.2 m³ 395.5 ft³

= Rear compartment capacity . . . . . . . . . . . . . . . . . . . . . . . . 2.4 m³ 84.7 ft³

= Radius of Action in Extended Range configuration (Supp 22) with reserves (subject to evaluation) . . . . . . . . 197 nm 365 km

n Maximum certified takeoff mass - MCTOM (basic). . . . . . 8,300 kg 18,298 lb

n Maximum mass for towing or taxying (basic) . . . . . . . . . . 8,350 kg 18,408 lb

n MCTOM with Weight Extension (Supplement 21) . . . . . . 8,600 kg 18,960 lg

n Maximum mass for towing or taxying (Supp 21). . . . . . . . 8,650 kg 19,070 lb

n VNE (‘never exceed speed’) at sea level ISA . . . . . . . . . 169 knots 313 km/hr

n Maximum landing gear operating airspeed. . . . . . . . . . . 130 knots 241 km/hr

n Maximum airspeed for IFR approach . . . . . . . . . . . . . . . 150 knots 278 km/hr

n Maximum run-on speed for emergency landing . . . . . . . . 60 knots 111 km/hr

n Maximum sideways airspeed . . . . . . . . . . . . . . . . . . . . . . 45 knots 45 km/hr

n Maximum rearwards airspeed. . . . . . . . . . . . . . . . . . . . . . 40 knots 74 km/hr

n Max takeoff & landing pressure altitude (target) . . . . . . . . . 8,000 ft 2,438 m

n Max operating altitude with Wt Extension (Supp 21) . . . . . 6,000 ft 2,000 m

n Maximum operating altitude (target) . . . . . . . . . . . . . . . . . 20,000 ft 6,096 m

n Minimum operating altitude (target). . . . . . . . . . . . . . . . . . -1,000 ft -305 m

n Operating temperature envelope at sea level . . . . . . . . . -40°C to +55°C or ISA+40°C

n Minimum air temperature for ground starting . . . . . . . . . . . . -40°C

n Sloping ground limitations . . . . . . . . . . . . . . . . . . . . . . . . Longitudinal and lateral 10°

n Limited icing clearance date (target) . . . . . . . . . . . . . . . . Mid 2015

n Full icing clearance date (target) . . . . . . . . . . . . . . . . . . . Mid 2016

Principal Operating Limitations


Emergency Exits and Push-out Windows

Cockpit door windows

Sliding cabin doorswith Type IV push-outemergency exit windows

Jettisonable bubble windows

Push-out emergencyexit windows


Starboard liferaft stowagePort liferaft stowage

Flotation Gear, Liferafts and ADELT

Flotation system(Sea state 6)

2 x 14 person liferafts with 21 person overload capacity

Liferafts

Each liferaft may be releasedmanually or electrically

Each liferaft has an ELT(JTSO-126)

ADELT (TSO-126)Crash Position Indicatoroperating on VHF 121.5 MHzand SARSAT 406.025 MHz

Cockpit control panel

Beacon release unit

Activated manually, ‘G’ orwater activated switches

Full COSPAS/SARSATcoverage - transmits lastknown GPS coordinates


Cabin General Configuration

Bubble windows

Full cabin sea tray

Stretcher

Four seats inthe front row

SAR equipment stowage

Access to equipmentstowage area from cabin

TrakkaBeam searchlight

FLIR turret under nose

Goodrichdual hoists

Two seats withfold-down backrestsallowing access torear equipment bay

Rear crewfoldable 17" display

Rear crewfoldable 17" display

Rear crew hard points


SAR AW189 8 SEATS

SAR AW1898 SEATS

1 STRETCHER CASE

Cabin Configuration Examples



2 x seats with folded backsproviding access to rear bay

SAR AW1894 FRONT ROW SEATS2 REAR ROW SEATS WITH FOLDING BACKRESTS2 NON-FOLDING REAR ROW SEATS

SAR AW1892 STRETCHER CASES



SAR AW1892-MAN MRT & EQUIPMENT

2 rear crew

2 MRT team

4 additional cabin seats

2 x stretchers in rear stowage

6 hill bags (0.6x0.35x0.3m) blue boxes

1 x stretcher (1.2x0.6x0.4m) brown box

4 x rope bags (0.6x0.3x0.15m) green boxes

1 x crag bag (0.6x0.3x0.15) green box



DrägerTI 500

incubator

SAR AW1891 INCUBATOR

SAR AW189CABIN DOME LIGHTS

NVG & WHITE


Cabin Configuration - Stretcher Operations

A A

Section AA

2.44 m8.0 ft

Cabin profile sectionwith 6 ft (1.83m)

man kneeling

1.4 m4.6 ft

SAR AW189LOADING THE

FERNO STRETCHERINTO THECABIN

1.75 m5 ft 9 in

View looking forwardfrom Section AA


Role Equipment - Dual Hoist Installation

The rescue hoist installation consists of twin Goodrich hoists mounted side-by-side above the right hand

sliding cabin door. The system is electrically powered and electronically controlled with an assembly of

limit switches providing a number of safety and automatic control features. The hoists are normally

controlled by the Winch Operator using one of the two NVG-compatible control pendants. However, the

pilot can also control the operation through the hoist control switch on the collective grip and this will

override winch operator’s input.

Safety features include:

l With the exception of the cable and hook, all moving parts of the hoist assembly are enclosed.

l Each D-lok hook consists of a double-latched, gated locking feature to prevent accidental disengagement of the load.

l A cable cutting system that enables the Winch Operator to cut the hoist cable in the event of an emergency which requires the hoist load to be jettisoned.

The leading characteristics are as follows:

l Electrical power requirement . . . . . . . . . . . . . . . . . . 115/200 VAC 3-phase 400 Hz

l Duty cycle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Continuous duty

l Rated load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 600 lb (272 kg)

l Limit load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2,100 lb (952 kg)

l Reel-in rated speed with 600 lb (272 kg) load . . . . . 320 ft/min (97.5 m/min)

l Typical cable speed with 300 lb (136 kg) load . . . . . 345 ft/min (105.2 m/min)

l Control pendant weight. . . . . . . . . . . . . . . . . . . . . . . 1.5 lb (0.68 kg)

l Ambient operating temperature range . . . . . . . . . . . -40°C to +60°C (-40°F to +140°F)

l Total cable length . . . . . . . . . . . . . . . . . . . . . . . . . . . 296 ft (90.2 m)

l Usable cable length . . . . . . . . . . . . . . . . . . . . . . . . . 290 ft (88.4 m)

Automatic cable acceleration, deceleration and stopping

To protect the hoist system, the limit switch assembly provides the following functions:

l Initial reel-out speed is limited to 75 ft/min (23 m/min) until the hook is extended beyond

10.5 ft (3.2 m)

l During extended reel-out, the cable speed is reduced to a nominal speed of 75 ft/min

(23 m/min) when approximately 7 wraps of cable are left on the drum.

l At extreme length, the hoist motor will stop to prevent cable reel-out beyond 290 ft (88.4 m)

l On reeling-in, the cable speed will be reduced to 75 ft/min (23 m/min) when the cable hook

is approximately 10 ft (3 m) from its stowed position. On continuing to reel-in, the cable

speed is further reduced to 35 ft/min (11 m/min) when the hook reaches around 2 ft (0.6 m)

from its stowed position.

l Limit switches stop hoist motor operation when the hook is in the stowed position.


Role Equipment - Dual Hoist Installation

Cable Cutters

Each hoist assembly incorporates an electronically initiated explosive cartridge actuated cable cutter

assembly. Cable cutter switches are located on the Winch Operator’s control panel and in the cockpit. A

manual ‘bolt cropper’ cable cutter is stowed adjacent to the Winch Operator’s station.

Hoist Control Pendants

Each control pendant comprises warning lights (CABLE, SLOW, TEMP and WTR), a variable REEL

IN/OUT thumb wheel, an intercom switch, a trim control switch and a cable length display.

l The variable speed cable reel IN/OUT switch is spring-loaded to the centre (off) position.

l The TEMP warning light indicates a hoist overtemperature condition.

l The WTR warning light will illuminate when the hover trim control switch is activated.

l The SLOW light illuminates whenever the hook is within 10 ft (3 m) from the full-in or full-out

settings of the limit switches.

l The CABLE light illuminates when a cable foul condition has been detected.

Winch Operator’s Hover Trim Control

l The 5-way Hover Trim Control on the pendant gives the Winch Operator limited lateral and

longitudinal groundspeed control when in the HOV mode (selected by the pilot).

Lights

l Two manoeuvrable hoist lights are installed under the helicopter, one on each side.

l Each light is independent of the

other and two control panels

are mounted in the cabin, one

for each lamp

Cable length

indicator

Cable reel

IN/OUT

Thumb

wheel

velocity

control

L

AFT

FWD

WTR

UP

DN

R

L

CABLE TEMP

SLOW WTR

8 8 8

Warning

indicators

Hover trim

control

Intercom

switch

(underneath)

CABLE TEMP

SLOW WTR

WTR

Winch Operator’s Pendant


Role Equipment - Avionics

The Selex ES Aircraft and Mission Management System (AMMS)

The AMMS is a powerful system designed to provide data processing features in rotary wing aircraft and

performs the following functions:

l Controls and monitors sensors (on the engines, rotors, fuel and hydraulic systems)

l Interfaces with the Electronic Flight Instrument System ( EFIS) and the Engine Instrument and Crew Alerting System (EICAS)

l Interfaces with the Communications, Navigation and Identification (CNI) Equipment

l Interfaces with the AFCS

l Provides the flight crew with digital maps, navigation and health data.

The AMMS is based on a core consisting of two identical computers synchronised and concurrently performing the same operations in a master/hot-standby architecture which allows, in case of failure of the Master, an automatic reconfiguration of all system functionalities resulting in high mission availability.

The Flight Management System (FMS) provides:

l Area navigation management

l Search pattern management

l Navigation database management

l Navigation display data management

l Helicopter and navigation performance computations

l Horizontal and vertical steering command generation for the AFCS

The Digital Map and symbol generation capability:

l Helicopter data upload and download

l Navigation data

l Comms data

l Map data

l Mission data

l HUMS data

l Maintenance data


The 4-Axis Autopilot With SAR Modes and Search Patterns

The autopilot is a 4-axis digital automatic flight control system with the following SAR modes that can be

initiated by the pilot through the AFCS control panel located in the cockpit central console and stopped

at any time by either pilot to recover manual lateral and/or vertical control of the helicopter.

l Transition Down (TD)

l Transition Down to the Hover (TD/H)

l Hover Point Approach (HPA)

l Transition Up (TU)

l Mark-on target (MOT)

l Winch Operator trim (WTR)

The FMS software provides flight guidance to enable SAR search patterns to be flown automatically and displayed on the cockpit screens. The following patterns may be selected by the pilot fhrough the FMS pages:


1 2 5 6 9 10 13 14

3 4 7 8 11 12

S ES

E

1

23

4 5

67

8

S1 2

34

5 6

78

9 10

11E

S 1

2

5

6

9

10

3

47

8

E

Initial trackInitial track

Initial trackInitial track

Creeping Ladder (Line Ahead) Search Expanding Square (Box) Search

Sector (Cloverleaf) Search Parallel Sweep Search

- Start point - End pointS E



Communications

l Wulfsberg V/UHF AM/FM Flexcomm II radio and control panel - covers FM frequencies from

29 to 960 MHz and AM frequencies from 29.7 to 400 MHz

l NAT NPX-138 VHF/FM radio with guard received capability (NVG-compatible control panel

in the cabin) providing 100 channels and a scanning facility. The radio operates on

frequencies from 138 to 173.975 MHz (the marine VHF band is 156 to 162.025 MHz)

l Polycon wireless system (VHF/UHF) with external antenna - two transceivers

l Polycon dock station for recharging one transceiver

l Trulink wireless intercom system - two water-tight transceivers with water-tight helmet

connection. This system is a full duplex wireless communication system working on the

2.4 GHz band that allows crew members to have wireless transceivers linked to the aircraft

intercom (ICS)

l NAT ACP53 Intercom System comprises two station boxes in the cockpit and three in the

cabin. Ten cabin sockets also provided in the cabin. The ICS is zoned as follows:

l Zone 1 for the pilot and co-pilot

l Zone 2 for the rear crew in the cabin

l Zone 3 for a medical team isolated from the front and rear crew members

The system is configurable to enable the following:

l All crew, medical team and other cabin occupants to the linked

l Cabin isolated from the cockpit

l Medical team isolated from the front and rear crew

The pilots can isolate themselves from the cabin but will always maintain the ability to

override any rearcrew ICS selections

l Rockwell Collins HF radio 2 - 30 MHz in 100 Hz steps with selectable RF output power

levels. It provides six emergency channels plus all 249 maritime RT network channels in

permanent non-volatile memory (HF-9031)

l SATCOM Iridium Flightcell DZMX (fleet tracking, email capability, L-Band transceiver) with

cockpit control panel. This system provides GPS automatic position reporting and allows the

crew to communicate with fixed telephones, mobile/cellular telephones or other users of

Satcom devices via the Iridium network.

l Iridium Phone Mount system with recharger (stand-alone hand portable SATCOM model

Iridium 9555 in the cabin)

l Provision for the installation of a Cobham Chelton Tetra transceiver in the interseat console

accessible from the cabin

l Standard ATC installation - two VHF/AM radios


Navigation

l Telephonics Weather/Search radar RDR-1500B+ (10" x 18" antenna and 180° scan) with an

NVG-compatible cockpit control panel. This radar can track up to 20 targets and provide the

following primary modes of operation:

l Weather Avoidance Modes (WX and WXA) providing continuous enroute precipitation-

related information

l Sea Surface Search and Terrain Mapping Mode (SRCH) to detect and display surface

targets down to a minimum tracking range of 150 m.

l Beacon, Detection and Navigation Mode (BCN) to interrogate, collect and locate beacon

transponders.

l Rockwell Collins TCAS II - detects the presence of nearby traffic equipped with TCAS and

provides visual (cockpit displays) and audible (through the ICS) resolution advisory

messages to the crew when traffic proximity becomes a safety threat.

l Dual digital moving map (DMAP) systems

l Cobham-Chelton Direction Finder with ‘On-Top’ Position Indicator provides the ability to

locate and steer to directional radio sources in the 30 to 470 MHz range. This system can

detect distress signals transmitted on 121.5 MHz (VHF), 156.525 MHz (GMDSS VHF DSC

Channel), 156.8 MHz (MAR), 243 MHz (UHF) and for Cospas-Sarsat beacon finding on

406.025/406.028 MHz frequencies. An ‘On-Top’ Position Indicator’ (OTPI) facility is provided

by the system which alerts the crew that the aircraft is directly on top of the received beacon.

The system features a multi-beacon mode of operation for detection of up to three SARBE 7

type V/UHF beacons and data message decoding received on Marine DSC and Cospas-

Sarsat channels.

l Helicopter Terrain Awareness Warning System (HTAWS). Using a colour coded display, this

system highlights areas of surrounding terrain above the aircraft’s current altitude that pose

a collision risk. In this event, audio warnings are heard by the pilots over the aircraft ICS.

HTAWS data is shown on the same screen as the route waypoint and leg displays

generated by the navigation computer.

l Saab R4A Transponder AIS integrated with the cockpit displays

l Standard ATC installation - two VOR/ILS/MB receivers

l One ADF receiver

l One DME

l One SBAS GPS (WAAS/EGNOS/MSAS)




Recorders

l Saab CR22 digital video HD recorder system with cockpit control panel and memory box.

Provides the ability to digitally record video and audio signals on to a removable Mass

Memory Module (MMC). It is designed to accommodate MMCs up to 100 GB memory

capacity. Recording time is dependent on video and audio compression rates which can be

adjusted by the user. The NVG-compatible control panel is located in the interseat console.

l A Sekai Electronic digital rescue hoist camera is installed on the right side of the airframe in

the proximity of the hoist rescue station and allows video recordings of winch operations to

be made.

l Tail fin camera - described later.

External Public Address System Loudspeaker

The 6-bell 700W external loudspeaker pack permits the crew to communicate with people on the

ground whilst remaining in flight. The External and Internal Public Address System (PA) installation

consists of an external loud speaker unit mounted under the tail cone and internally mounted

speakers. The loud speakers are controlled by a control panel mounted in the interseat console .

This panel allows selection of internal (INT) or external

(EXT) speakers, siren tone (WAIL/YELP), volume

control and selection of PA or radio re-broadcast

(provisional only).

The control panel is interfaced with the aircraft ICS

audio panel. By selecting the ICS rotary switch to the PA

position, the pilot or copilot microphone messages may

be broadcast internally or externally. The PA panel is

NVIS green compliant.

VOL PA WAIL EXT

RADIO YELP INT


Role Equipment - FLIR

The Star Safire 380 HD FLIR system is a remote controlled day/night high resolution,

infrared (IR) imaging system with colour video. The system consists of a gyro-stabilised

Turret-FLIR Unit (TFU) mounted under the nose of the helicopter, a system contol unit

which consists of a mobile Universal Hand Control Unit

(UHCU) with all the controls necessary to operate the

FLIR turret and systems, and a System Control Unit

(SCU).

The FLIR Line of Sight (LOS), corresponding to the centre

of the image, can be directed to any position within the

Field of Regard (FOR) which is 30° to -120° in elevation

and 360° in azimuth from the forward position.

The FLIR imager incorporates:

l A short wave infrared camera (SWIR)

l A high definition electro-optical camera (HDEO)

l A high definition infrared camera (HDIR)

l A day/low light/near IR colour camera (HDLL)

l A Class 1 eye=safe laser range finder (ESLRF)

The FLIR/TV is interfaced with the Flight Management System to

receive the present position and UTC information and provides video

output that can be presented on the cockpit and mission console

displays.

The IR camera has five optical Fields of View and produces images in

total darkness or in low visibility or low contrast conditions. The FLIR

cameras provide video outputs that can be monitored on either pilot’s

Multi-Function Display. Either IR or EO images can be selected

independently on the pilot’s or copilot’s MFD or both images in

reduced format. Image blending is also enabled.

The FLIR can also be interfaced with the TrakkaBeam A300 for slaving commands and with the

RDR-1500B+ radar system to receive a position-point slaving command.

To prevent inadvertent firing of the ESLRF, the laser safety lock unit (LIU) incorporates an ARM

switch and a Weight-On-Wheels switch ensures that the laser cannot be used on the ground.

UHCU

TFU


Role Equipment - External Lighting

The SAR AW189 is equipped with comprehensive external and internal lighting systems designed

to provide appropriate illumination during all phases of a search and rescue operation. Externally,

the aircraft has an array of powerful fixed lights to illuminate the rescue scene. These are

augmented by steerable landing and search lights. The high intensity TrakkaBeam A800

searchlight mounted on the port side of the fuselage may be controlled by the rear crew in

conjunction with the EO and IR cameras to throw an intense beam exactly on the required location.

It is slaved to the FLIR Star Safire 380 HD.

The TrakkaBeam A800

l Bespoke Xenon lamp technology

l Optical elements provide effective collimation of the beam and reduced stray light. This design eliminates the ‘black hole’ often encountered in a narrow beam.

l Up to six different filters can be activated at the touch of a button by the operator.

l Different filter options reduce the glare from fog or white sand.

TrakkaBeam A800 characteristics

l Power (watts) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 800

l Total lumens . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22,500

l Beam width (focus) . . . . . . . . . . . . . . . . . . . . . . . . . . 4° - 13.3°

l Diameter at 3,300 ft . . . . . . . . . . . . . . . . . . . . . . 249 ft (76 m) 40% of peak illuminance

l Recycle time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Not required

l Gimbal control. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 axis remote

l Azimuth rotation . . . . . . . . . . . . . . . . . . . . . . . . . . . . +180° / -180° (non-continuous)

l Elevation rotation . . . . . . . . . . . . . . . . . . . . . . . . . . . +35° / -90°

l Starting time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 second

Other External Lights

l 2 fixed flood lights under the belly of the helicopter

l Main and tail rotor lighting system. This system consists of five dedicated LED type

lights:

l Two lights located in the sponson area provide illumination of the tail rotor and the

main rotor blade tips in a rearward direction, each providing a conical beam with an

angle of approximately 45°

l Three lights located on the top of the airframe illuminate the main rotor blade tips

each providing a conical beam with an angle of 30°

l 2 swivelling and retractable hoist lights installed under the helicopter, one on each side


Internal Lighting

The cabin is equipped with a lighting system specifically designed to provide appropriate

illumination for all circumstances encountered during a SAR mission including NVG operations and

the provision of medical attention to survivors. and casualties:

l 6 dome ceiling dome lights (NVG & white)

l 6 cabin emergency lights incorporated in the dome lights

l 4 detachable ‘cockpit-type’ utility lights (NVG & white) in the 4 corners of the cabin

l Helicopter Emergency Exits Light System (HEELS). This system is activated in

emergency conditions to facilitate the egress of the cockpit and cabin occupants when

the cabin becomes submerged, partially or completely, as a consequence of a

ditching. It consists of luminescent strip lights which indicate the extent of each

window and door. Five batteries power the system which is activated by water

sensors.

Role Equipment - Internal Lighting

(kg) (lb)

1085 2392

Tank

Total fuel capacity 2069 4561

Main tanks (2)

984 2169Belly tank

Fuel Tank Capacities (nominal)

Fuel Tanks in Extended Range Configuration

Two main tanks

Extended rangebelly tank

(Three fuel cells)

HM COASTGUARD

COASTGUARD RESCUE


Safety Features

w Damage and corrosion resistant composite blades

w Bird strike resistant cockpit windscreens

w Windscreen washing system

w Full Authority Digital Engine Control (FADEC)

w High Intensity Radiated Field (HIRF) and Lightning Electromagnetic Pulse (LEMP) resistant design.

w Baggage bay smoke detection

w Wire strike protection cutter mounted above the cockpit

w High power to weight ratio giving excellent single engine performance

w Relatively high main and tail rotors provide a safer environment for ground personnel

w Hydraulically actuated rotor brake

w Enhanced 4-axis digital autopilot with SAR modes

w Solid state Cockpit & Voice Flight Data Recorder (CVFDR) with underwater locator beacon

w Tail fin camera (see next page)

w Engines and APU fire detection and extinguishing systems

w Heated engine intakes and fuel anti-icing systems

w Telephonics RDR-1500B+ colour weather radar

w Cockpit & cabin fire hand extinguishers (EU OPS 3 compliant)

w Dual anti-collision lights

w Central maintenance computer

w Emergency flotation gear with automatic deployment (sea state 6)

w Automatically Deployed Emergency Locator Transmitter (ADELT TSO126 standard) with GPS interface and GPS integrated

w Dual external liferafts each with 21 person capacity including PLB (JTSO-126 standard)

w Main gearbox 50 minute ‘run-dry’ capability

w Engine turbine burst containment

w Crashworthy cockpit and cabin seats

w Health & Usage Monitoring System

w Flight Data Monitoring (FDM)

w Helicopter Terrain and Warning System (HTAWS)

w Traffic Collision Avoidance System (TCAS II)

w SkyConnect satellite communications & flight tracking

w Dual redundant architecture for hydraulic, electrical, fuel and avionics data bus systems

w Two independent crashworthy main fuel cells

w One pressure (RHS) & two gravity refuelling filling points (LHS & RHS)

w Cabin / cockpit emergency exit lights - Helicopter Emergency Egress System (HEELS)

w Curtain separation wall between the cockpit and the cabin

w Fail safe construction in vital airframe structural areas


HM COASTGUARD

COASTGUARD RESCUE

The tail fin camera enables the flight crew in the cockpit to check visually the area of the engine bays and the rear compartment doors. The image is displayed on one of the four cockpit Multi Mission Displays (MMD) when required.

Tail Fin CameraApproximateCoverage

48° Vertical field of view

62° Horizontal field of view


l Comfortable seats with 4-point safety harness and inertia reel

l Environmental control system provides forced ventilation, heating, and air conditioning

l Reduced vibration levels resulting from the 5-bladed main rotor system

l Cabin step to facilitate entry and exit

l Full de-icing system (from mid-2016)

l Cargo hook (max load 2,722 kg / 6,000 lb)

l The Aircraft Monitoring & Management System (AMMS) provides the following functions:

§ Helicopter system status control & monitoring

§ Warning, caution & advisory alarm generation

§ Communication & navigation management

§ Helicopter maintenance management

§ Helicopter database upload/download

§ Health, usage and diagnostic monitoring

l Hydraulic System:

§ Dual independent, redundant systems

§ Three main transmission driven mechanical pumps

§ One electric motor driven hydraulic pump

§ Three main rotor dual servos

l Underfloor auxiliary fuel cells

Crew Comfort Features

Optional Capabilities

Aircraft Equipment & Systems


l Engines:

§ Two GE CT7-2E1 turboshaft engines with integrated particle separator

§ One Microturbo e-APU 60kW Auxiliary Power Unit

§ Two independent dual-channel FADECs with auto-start, auto relight, engine controls for normal, emergency and training operations

§ Electronic ECU for the APU

l Fuel System:

§ Two submerged booster pumps in fuel tanks

§ Engine crossfeed valves

l Electrical System:

§ DC / AC primary power generation system provided by 3 independent 25kVA starter generators

§ Three Transformer Rectifier Units

§ Cabin power outlets (2 x AC and 2 x DC)

l Cockpit Display System:

§ Dual pilot IFR instrumentation on four active matrix 10" x 8" (254 x 203 mm) LCD glass displays:

© Two Primary Flight Displays (PFD)

© Two Multifunction Mission Displays (MMD)

§ One integrated standby instrument system

§ Two radar altimeters

l Radio Communications & Navigation Systems:

§ Dual Flight Management Systems

§ Two VHF-AM radios

§ Two NAV (VOR/ILS/MKR) Receivers

§ One ADF

§ One DME

§ One transponder with Enhanced Surveillance Mode (Mode S)

§ Dual Satellite-Based Augmentation System GPS (WAAS/EGNOS/MSAS)

§ VHF-FM NTX-138 NAT radio

Aircraft Equipment & Systems(continued)

agustawestland aw189 search and rescue -...

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